Airworthiness Directives; Airbus Airplanes, 47537-47543 [2013-18774]
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
47537
FIGURE 1 TO PARAGRAPH (c)—TGB RADIAL GEARSHAFT P/N 1995M24P02 S/N’ S—Continued
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(d) Unsafe Condition
This AD was prompted by reports of
three failures of TGB radial gearshafts
which resulted in in-flight shutdowns
(IFSDs). We are issuing this AD to
prevent failure of the TGB radial
gearshaft, which could result in IFSD of
one or more engines, loss of thrust
control, and damage to the airplane.
(e) Compliance
(1) Comply with this AD within the
compliance times specified, unless
already done.
(2) Before further flight after the
effective date of this AD, do not operate
the airplane if more than one installed
engine has a TGB radial gearshaft P/N
and S/N listed in Figure 1 to paragraph
(c) of this AD.
(f) Mandatory Terminating Action
No later than 60 days after the
effective date of this AD, as terminating
action to the requirements of paragraph
(e) of this AD, replace all TGB radial
gearshafts identified in Figure 1 to
paragraph (c) of this AD that are
installed on an airplane with TGB radial
gearshafts that are eligible for
installation.
(g) Prohibition on Operation
Sixty days after the effective date of
this AD, do not operate any airplane
that has an engine installed that has a
TGB radial gearshaft P/N and S/N listed
in Figure 1 to paragraph (c) of this AD.
tkelley on DSK3SPTVN1PROD with RULES
(h) Definition
For the purposes of this AD, a TGB
radial gearshaft eligible for installation
is:
(1) A TGB radial gearshaft P/N and S/
N, not listed in this AD or
(2) A TGB radial gearshaft with an S/
N listed in paragraph (c) of this AD with
part number 1995M24P04, 2205M61P01
or 2205M61P02.
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(i) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification
Office, FAA, may approve AMOCs for
this AD. Use the procedures in 14 CFR
39.19 to make your request.
(j) Related Information
(k) Material Incorporated by Reference
None.
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Issued in Burlington, Massachusetts, on
July 25, 2013.
Frank P. Paskiewicz,
Acting Director, Aircraft Certification Service.
[FR Doc. 2013–18840 Filed 8–5–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
(1) For more information about this
AD, contact Carlos Fernandes,
Aerospace Engineer, Engine
Certification Office, FAA, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7189; fax: 781–
238–7199; email:
carlos.fernandes@faa.gov.
(2) GE GE90–100 Series Alert Service
Bulletin No. GE90–100 S/B 72–A0568,
Revision 0, dated July 10, 2013; GE
GE90–100 Series Service Bulletin (SB)
No. GE90–100 S/B 72–0569, Revision 0,
dated July 19, 2013; GE GE90–100
Series SB No. GE90–100 S/B 72–0563,
Revision 0, dated June 21, 2013, and
Revision 1, dated July 10, 2013; GE
GE90 SB No. GE90 S/B 72–1066,
Revision 0, dated June 21, 2013; and GE
GE90 SB No. GE90 S/B 72–1091,
Revision 0, dated June 11, 2013, can be
obtained from GE using the contact
information in paragraph (j)(3) of this
AD.
(3) For service information identified
in this AD, contact General Electric
Company, One Neumann Way, Room
285, Cincinnati, OH; phone: 513–552–
3272; email: geae.aoc@ge.com.
(4) You may view this service
information at the FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1033; Directorate
Identifier 2010–NM–266–AD; Amendment
39–17504; AD 2013–13–16]
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) 2005–07–
04 for all Airbus Model A330–200 and
–300 series airplanes, and Model A340–
200 and –300 series airplanes. AD 2005–
07–04 required repetitive inspections to
detect discrepancies of the transfer
tubes and the collar of the ball nut of the
trimmable horizontal stabilizer actuator
(THSA), and corrective action if
necessary; repetitive inspections for
discrepancies of the ball screw
assembly, and corrective action if
necessary; 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
removes certain inspections, revises
certain actions, and adds airplanes to
the applicability. This AD was
prompted by several reports of
SUMMARY:
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
disconnection of the transfer tube from
the ball nut of the THSA. We are issuing
this AD to prevent degraded operation
of the THSA, which could result in
reduced controllability of the airplane.
DATES: This AD becomes effective
September 10, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 10, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of May 4, 2005 (70 FR 16104,
March 30, 2005).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
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:
tkelley on DSK3SPTVN1PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. The
NPRM was published in the Federal
Register on October 2, 2012 (77 FR
60075), and proposed to supersede AD
2005–07–04, Amendment 39–14028 (70
FR 16104, March 30, 2005). (AD 2005–
07–04 superseded AD 2001–11–09,
Amendment 39–12252 (66 FR 31143,
June 11, 2001).) The NPRM proposed to
correct an unsafe condition for the
specified products. The European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2010–0192 (corrected), dated October
11, 2010; and EASA Airworthiness
Directive 2010–0193 (corrected), dated
October 11, 2010; (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. 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.
This condition is caused by water ingress
into the ball-nut resulting in the jamming of
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the ball transfer circuit when the water
freezes.
If the three (independent) ball circuits fail,
then the THSA will operate on a fail-safe nut.
This nut (which operates without balls)
would then jam after several movements on
the screw of the THSA.
This degraded operation is not detectable
in the cockpit by the crew as long as the
THSA does not jam and could damage the
ball screw and the fail-safe nut.
´
To detect this unsafe condition, [Direccion
´
General de Aviacion Civil] DGAC France AD
F–2001–356 [and F–2001–357] was issued to
require repetitive inspections of the transfer
tubes and their collars in order to detect at
an early stage any distortion or initiation of
disconnection.
Further to a new case of transfer tube
disconnection, * * * [revised DGAC ADs]
required an additional repetitive greasing
task with reinforcement of the ball-nut
maintenance greasing instructions.
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 ECAM
[electronic centralized aircraft monitor]. In
this case a mandatory inspection of the
THSA is required before the next flight.
DGAC France AD F–2002–038 [and F–
2002–037] required application of a final fix
(related to inspection and greasing task
required by DGAC France AD F–2001–356
[and F–2001–357]) for the THSA P/N 47172
by application of Airbus modification 49590/
Service Bulletin (SB) A330–27–3085 [or SB
A340–27–4089]. It changes the THSA P/N
from 47172 to 47172–300.
Later on, DGAC France AD F–2002–414R3
replaced the DGAC AD France F–2001–
356R2 and F–2002–038 [and DGAC France
AD F2002–415R2 superseded DGAC France
ADs F–2001–357R2 and F–2002–037]
requiring:
—the repetitive [detailed] inspection [for
discrepancies] of all THSA P/N in service
[for integrity of the primary and secondary
load path and check the Checkable Shear
Pins (CSPs)], and
—the lubrication of some THSA P/N, and
—the replacement of THSA P/N 47172,
47147–400 and 47147–2XX/–3XX
[DGAC France AD F–2002–414R3 and F–
2002–415R2 correspond to FAA AD 2005–
07–04, Amendment 39–14028 (70 FR 16104,
March 30, 2005).]
Airbus has later introduced 4 new THSA
P/N (47172–500, 47172–510, 47172–520 and
47172–530).
This [EASA] AD retains the requirements
of DGAC France AD F–2002–414R3 [and F–
2002–415R2], which is superseded, and
requires repetitive inspections and
lubrications of the new THSA P/N.
The repetitive inspection and lubrication
requirements for THSA P/N 47172–520 and
47172–530 shall [also] be included in the
next Airworthiness Limitation Section (ALS)
Part 4 revision.
*
*
*
*
*
Corrective actions include replacing
the THSA with a new THSA if cracks,
dents, or corrosion are found, or if the
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feeler gage has failed at any of the four
gaps. Other corrective action includes
using a method approved by the FAA or
the EASA (or its delegated agent) for a
finding of metallic debris, loose nut,
damaged or missing lock washers, pins
and parts, or incorrect installation of
items. AD 2005–07–04, Amendment 39–
14028 (70 FR 16104, March 30, 2005),
required repetitive inspections for
discrepancies. This AD requires, for
certain airplanes, repetitive inspections
for the integrity of the primary and
secondary load path, and the CSPs. The
unsafe condition is the degraded
operation of the THSA, which could
result in reduced controllability of the
airplane. You may obtain further
information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Request To Use Later Document
Revision
Delta Airlines (Delta) requested that
paragraph (j)(2) of the NPRM (77 FR
60075, October 2, 2012) refer to Airbus
A330 Airworthiness Limitations Section
(ALS) Part 4—Ageing Systems
Maintenance, Revision 03, dated
September 9, 2011; instead of Revision
02, dated December 16, 2009. Delta
stated that Revision 03 of that ALS
specifies the 1,000 flight-hour
lubrication threshold and repetitive
interval that are specified in paragraph
(j)(2) of the NPRM, whereas Revision 02
of this ALS specifies 700 flight hours for
the lubrication threshold and repetitive
interval.
We agree that Airbus A330
Airworthiness Limitations Section
(ALS) Part 4—Ageing Systems
Maintenance, Revision 03, dated
September 9, 2011, correctly specifies
the lubrication threshold and repetitive
interval. We have changed paragraph
(j)(2) of this AD accordingly. In
addition, we have changed paragraph
(j)(2) of this AD to reference Airbus
A340 ALS Part 4—Ageing Systems
Maintenance, Revision 02, dated
October 12, 2011; and Revision 03,
dated November 15, 2012; for the same
reason.
Request To Change Wording
Delta requested that we change the
wording in paragraph (l) of the NPRM
(77 FR 60075, October 2, 2012), which
states ‘‘For airplanes identified in
paragraph (k) of this AD.’’ The
commenter asked that the wording
‘‘identified in’’ be replaced with
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‘‘affected by.’’ The commenter provided
no reason for the change.
We disagree to change the wording in
paragraph (n) in this AD (identified as
paragraph (l) in the NPRM (77 FR
60075, October 2, 2012)) as requested by
the commenter. However, we have
moved the content of paragraphs (k)(1),
(k)(2), and (k)(3) of the NPRM to new
paragraph (l) in this AD to clarify the
actions and affected airplanes. We have
also moved the content of paragraph
(k)(6) of the NPRM to new paragraph
(m) of this AD, and re-identified
succeeding paragraphs accordingly.
Finally, in paragraph (n) of this AD, we
revised the wording to describe the
affected airplanes.
Request To Include Additional Part
Number
Delta requested that we include THSA
P/N 47172–520 and P/N ‘‘47127–530’’
in paragraph (m) of the NPRM (77 FR
60075, October 2, 2012) as applicable
part numbers for Model A330 series
airplanes.
We disagree to include THSA P/N
47127–530 as there is no such part
number. We infer that the commenter
meant to specify THSA P/N 47172–530.
THSA P/N 47172–520 and P/N 47172–
530 are not included in the MCAI.
However, all necessary tasks for those
THSA part numbers are contained in
Airbus A330 Airworthiness Limitations
Section (ALS) Part 4—Ageing Systems
Maintenance, Revision 03, dated
September 9, 2011; and Airbus A340
ALS Part 4—Ageing Systems
Maintenance, Revision 02, dated
October 12, 2011, and Revision 03,
dated November 15, 2012. The FAA
NPRMs to mandate these ALS Part 4
documents are pending at this time.
Therefore, we have not changed this AD
in this regard.
tkelley on DSK3SPTVN1PROD with RULES
Request To Consider Another EASA AD
Corinne Dayde stated that she
‘‘Cannot see how EASA 2012–0061 is
considered.’’
We are considering addressing EASA
AD 2012–0061R1, dated November 30,
2012, in a separate FAA AD. We have
not changed this AD in this regard.
Conclusion
We reviewed the available data,
including the comments received, 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 changes:
• Are consistent with the intent that
was proposed in the NPRM (77 FR
60075, October 2, 2012) for correcting
the unsafe condition; and
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• Do not add any additional burden
upon the public than was already
proposed in the NPRM (77 FR 60075,
October 2, 2012).
Costs of Compliance
We estimate that this AD will affect
about 33 products of U.S. registry.
The actions that are required by AD
2005–07–04, Amendment 39–14028 (70
FR 16104, March 30, 2005), and retained
in this AD take up to 36 work-hours per
product, at an average labor rate of $85
per work-hour. Based on these figures,
the estimated cost of the retained
actions is up to $3,060 per product.
We estimate that it will take about 2
work-hours per product to comply with
the new basic requirements of this AD.
The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $5,610, or $170 per
product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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;
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47539
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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)
2005–07–04, Amendment 39–14028 (70
FR 16104, March 30, 2005), and adding
the following new AD:
■
2013–13–16 Airbus: Amendment 39–17504.
Docket No. FAA–2012–1033; Directorate
Identifier 2010–NM–266–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective September 10, 2013.
(b) Affected ADs
This AD supersedes AD 2005–07–04,
Amendment 39–14028 (70 FR 16104, March
30, 2005).
(c) Applicability
This AD applies to all Airbus Model A330–
201, –202, –203, –223, –223F, –243, –243F,
–301, –302, –303, –321, –322, –323, –341,
–342, and –343 airplanes; and Model A340–
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211, –212, –213, –311, –312, and –313
airplanes; certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 27: Flight Controls.
(e) Reason
This AD was prompted by several reports
of disconnection of the transfer tube from the
ball nut of the trimmable horizontal stabilizer
actuator (THSA). We are issuing this AD to
prevent degraded operation of the THSA,
which could result in reduced controllability
of the airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Modification or Replacement
This paragraph restates the requirements of
paragraph (g) of AD 2005–07–04,
Amendment 39–14028 (70 FR 16104, March
30, 2005). Except for Model A330–223F and
–243F airplanes: Within 24 months after May
4, 2005 (the effective date of AD 2005–07–
04), modify the ball nut of each THSA by
doing paragraph (g)(1) or (g)(2) of this AD, as
applicable.
(1) For THSAs having part number (P/N)
47172: Modify the ball nut of the THSA, or
replace the existing THSA with a serviceable
part having P/N 47172–300; in accordance
with Airbus Service Bulletin A330–27–3085
(for Model A330 series airplanes) or A340–
27–4089 (for Model A340–313 series
airplanes), both Revision 02, both dated
September 5, 2002; as applicable.
Note 1 to paragraph (g)(1) of this AD:
Airbus Service Bulletins A330–27–3085 and
A340–27–4089, both Revision 02, both dated
September 5, 2002, refer to TRW
Aeronautical Systems Service Bulletin
47172–27–03, dated October 24, 2001 (which
is not incorporated by reference in this AD),
as additional guidance for accomplishing the
modification of the ball nut of the THSA.
(2) For THSAs having P/N 47147–200,
–210, –213, –300, –303, –350, or –400:
Modify the ball nut of the THSA, or replace
the existing THSA with an improved part
having P/N 47147–500; as applicable; in
accordance with Airbus Service Bulletin
A330–27–3093 (for Model A330 series
airplanes) or A340–27–4099 (for Model
A340–200 and –300 series airplanes), both
Revision 01, both dated September 5, 2002;
as applicable.
Note 2 to paragraph (g)(2) of this AD:
Airbus Service Bulletins A330–27–3093 and
A340–27–4099, both Revision 01, both dated
September 5, 2002, refer to TRW
Aeronautical Systems Service Bulletin
47147–27–10, dated June 27, 2002 (which is
not incorporated by reference in this AD), as
additional guidance for accomplishing the
modification of the ball nut of the THSA.
(h) Retained Previous/Concurrent
Requirements
This paragraph restates the requirements of
paragraph (h) of AD 2005–07–04,
Amendment 39–14028 (70 FR 16104, March
30, 2005).
(1) Except for Model A330–223F and
–243F airplanes, prior to or concurrently
with accomplishing the requirements of
paragraph (g)(2) of this AD, do all of the
actions specified in the Accomplishment
Instructions of the applicable Airbus service
bulletins listed in table 1 or 2 to paragraph
(h)(1) of this AD, as applicable, in accordance
with those service bulletins.
Note 3 to paragraph (h)(1) of this AD:
Airbus Service Bulletin A330–27–3093,
Revision 01, dated September 5, 2002,
specifies that the actions in Airbus Service
Bulletin A330–27–3052 be accomplished
previously or concurrently. Airbus Service
Bulletin A330–27–3052, Revision 03, dated
December 5, 2001, specifies that the actions
in Airbus Service Bulletins A330–27–3007,
A330–27–3015, A330–27–3047, A330–27–
3050, and A330–55–3020 be accomplished
previously or concurrently.
Note 4 to paragraph (h)(1) of this AD:
Airbus Service Bulletin A340–27–4099,
Revision 01, dated September 5, 2002,
specifies that the actions in Airbus Service
Bulletin A340–27–4059 be accomplished
previously or concurrently. Airbus Service
Bulletin A340–27–4059, Revision 03, dated
December 5, 2001, specifies that the actions
in Airbus Service Bulletins A340–27–4007,
A340–27–4025, A340–27–4054, A340–27–
4057, and A340–55–4021 be accomplished
previously or concurrently.
TABLE 1 TO PARAGRAPH (h)(1) OF THIS AD—RETAINED PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A330
SERIES AIRPLANES
Airbus service
bulletin—
Revision
level—
Date—
Main action—
Additional source of guidance (not incorporated by reference in this AD)—
Samm
Avionique Service Bulletin
SC5300–27–24–01, dated April 15,
1994.
Lucas Aerospace Service Bulletin 47147–
27–02, Revision 1, dated January 31,
1996.
Lucas Aerospace Service Bulletin 47147–
27–04, Revision 1, dated June 20,
1997.
Lucas Aerospace Service Bulletin 47147–
27–05, dated November 8, 1996.
Lucas Aerospace Service Bulletin 47147–
27–07, dated May 4, 1998.
None.
A330-27-3007 .....
01
September 18, 1996 ....
Replace rudder servo controls with modified parts.
A330-27-3015 .....
................
June 7, 1995 ................
A330-27-3047 .....
01
November 26, 1997 .....
Modify the control valve detent and the
jamming protection device on the
THSA.
Replace hydraulic motors on the THSA
with new parts.
A330-27-3050 .....
................
November 15, 1996 .....
A330-27-3052 .....
03
December 5, 2001 .......
A330-55-3020 .....
01
October 21, 1998 .........
Replace mechanical input shaft for THSA
with modified part.
Replace THSA with a modified THSA ......
Perform a general visual inspection of the
THSA screw jack fitting assembly for
correct installation of a washer; and
correctly install washer as applicable.
tkelley on DSK3SPTVN1PROD with RULES
TABLE 2 TO PARAGRAPH (h)(1) OF THIS AD—RETAINED PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A340
SERIES AIRPLANES
Airbus service
bulletin—
Revision
level—
Date—
Main action—
Additional source of guidance (not incorporated by reference in this AD)—
A340-27-4007 .....
................
April 7, 1994 .................
A340-27-4025 .....
................
June 7, 1995 ................
Replace hydraulic motors on the THSA
with new parts.
Modify the control valve detent and the
jamming protection device on the
THSA.
Lucas Aerospace Service Bulletin 47147–
27–01, dated May 4, 1998.
Lucas Aerospace Service Bulletin 47147–
27–02, Revision 1, dated January 31,
1996.
VerDate Mar<15>2010
19:12 Aug 05, 2013
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47541
TABLE 2 TO PARAGRAPH (h)(1) OF THIS AD—RETAINED PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A340
SERIES AIRPLANES—Continued
Airbus service
bulletin—
Revision
level—
Date—
Main action—
Additional source of guidance (not incorporated by reference in this AD)—
Lucas Aerospace Service Bulletin 47147–
27–04, Revision 1, dated June 20,
1997.
Lucas Aerospace Service Bulletin 47147–
27–05, dated November 8, 1996.
Lucas Aerospace Service Bulletin 47147–
27–07, dated May 4, 1998.
None.
A340-27-4054 .....
01
November 26, 1997 .....
Replace hydraulic motors on the THSA
with new parts.
A340-27-4057 .....
................
November 15, 1996 .....
A340-27-4059 .....
03
December 5, 2001 .......
Replace mechanical input shaft for THSA
with modified part.
Replace THSA with a modified THSA ......
A340-55-4021 .....
01
October 21, 1998 .........
(2) For the purposes of this AD, a general
visual inspection is: A visual examination of
an interior or exterior area, installation, or
assembly to detect obvious damage, failure,
or irregularity. This level of inspection is
made from within touching distance unless
otherwise specified. A mirror may be
necessary to ensure visual access to all
surfaces in the inspection area. This level of
inspection is made under normally available
lighting conditions such as daylight, hangar
lighting, flashlight, or droplight and may
require removal or opening of access panels
or doors. Stands, ladders, or platforms may
be required to gain proximity to the area
being checked.
tkelley on DSK3SPTVN1PROD with RULES
(i) Retained Credit for Previous Actions
(1) This paragraph provides credit for the
requirements of paragraph (g)(1) of this AD,
if those actions were performed before May
4, 2005 (the effective date of AD 2005–07–04,
Amendment 39–14028 (70 FR 16104, March
30, 2005)), using Airbus Service Bulletin
A330–27–3085 (for Model A330 series
airplanes) or A340–27–4089 (for Model
A340–313 series airplanes), both Revision 01,
both dated January 23, 2002 (which are not
incorporated by reference in this AD), as
applicable.
(2) This paragraph provides credit for the
requirements of paragraphs (g)(2) of this AD,
if those actions were performed before May
4, 2005 (the effective date of AD 2005–07–04,
Amendment 39–14028 (70 FR 16104, March
30, 2005)), using Airbus Service Bulletin
A330–27–3093 (for Model A330 series
airplanes) or A340–27–4099 (for Model
A340–200 and –300 series airplanes), both
dated June 27, 2002 (which are not
incorporated by reference in this AD), as
applicable.
(j) New Repetitive Greasing Procedure
(1) Within 700 flight hours after the
effective date of this AD, or within 700 flight
hours after the date of the last lubrication,
whichever occurs later; and thereafter at
intervals not to exceed 700 flight hours from
the last lubrication of the trimmable
horizontal stabilizer (THS) actuator ball
screw nut: Perform Task 27.40.00/02,
Lubrication of THS Actuator Ball Screw Nut,
in accordance with Airbus A330
Maintenance Review Board Report (MRBR),
Revision 12, dated July 1, 2010 (for Model
A330 series airplanes); or Airbus A340
VerDate Mar<15>2010
19:12 Aug 05, 2013
Jkt 229001
Perform a general visual inspection of the
THSA screw jack fitting assembly for
correct installation of a washer; and
correctly install washer as applicable.
MRBR, Revision 12, dated July 1, 2010 (for
Model A340 series airplanes); on all THSAs.
(2) For airplanes identified in paragraphs
(j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD, as
applicable, lubrication of the THS actuator
ball screw nut performed at a threshold of
1,000 flight hours and a repetitive interval
not exceeding 1,000 flight hours, in
accordance with Task 274400–00002–1–E,
Lubrication of the THSA Ball Nut, of Airbus
A330 Airworthiness Limitations Section
(ALS) Part 4—Ageing Systems Maintenance,
Revision 03, dated September 9, 2011 (for
Model A330 series airplanes); or 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, or Revision 03, dated
November 15, 2012 (for Model A340–200 and
–300 series airplanes); is acceptable for
compliance with the requirements of
paragraph (j)(1) of this AD.
(i) Airplanes on which Airbus
Modifications 52269, 56056, and 55780 have
been done in production.
(ii) Model A330 series airplanes on which
the actions specified in Airbus Mandatory
Service Bulletin A330–27–3137, dated March
20, 2007, or Revision 01, dated December 6,
2007, or Revision 02, dated January 18, 2010;
and Airbus Mandatory Service Bulletin
A330–92–3046, Revision 04, dated July 16,
2010, or Revision 05, dated November 7,
2011; which are not incorporated by
reference in this AD; have been done in
service.
(iii) Model A340–200 and –300 series
airplanes on which the actions specified in
Airbus Mandatory Service Bulletin A340–27–
4136, dated March 20, 2007, Revision 01,
dated December 6, 2007, or Revision 02,
dated February 24, 2010; and Airbus
Mandatory Service Bulletin A340–92–4056,
Revision 03, dated July 16, 2010; which are
not incorporated by reference in this AD;
have been done in service.
(k) New Repetitive Inspections of the Ball
Screw Assembly and Corrective Actions
For airplanes other than those identified in
paragraphs (l)(1), (l)(2), and (l)(3) of this AD:
Do the applicable actions specified in
paragraphs (k)(1) and (k)(2) of this AD within
700 flight hours after the effective date of this
AD, and repeat the inspection thereafter at
intervals not to exceed 700 flight hours.
PO 00000
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Fmt 4700
Sfmt 4700
(1) For airplanes on which the actions
specified in Airbus Mandatory Service
Bulletin A330–27–3137, dated March 20,
2007, Revision 01, dated December 6, 2007,
or Revision 02, dated January 18, 2010 (for
Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–27–4136,
dated March 20, 2007, Revision 01, dated
December 6, 2007, or Revision 02, dated
February 24, 2010 (for Model A340–200 and
–300 series airplanes); none of which are
incorporated by reference in this AD; have
been done: Do the applicable detailed
inspection of the ball screw assembly for
integrity of the primary and secondary load
path and check the checkable shear pins
(CSP), and do all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–27–3102,
Revision 08, dated December 6, 2007 (for
Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–27–4107,
Revision 08, dated December 6, 2007 (for
Model A340–200 and –300 series airplanes);
except as required by paragraph (m) of this
AD. Do all applicable corrective actions
before further flight.
(2) For airplanes on which the actions
specified in Airbus Mandatory Service
Bulletin A330–27–3137, dated March 20,
2007, Revision 01, dated December 6, 2007,
or Revision 02, dated January 18, 2010 (for
Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–27–4136,
dated March 20, 2007, Revision 01, dated
December 6, 2007, or Revision 02, dated
February 24, 2010 (for Model A340–200 and
–300 series airplanes); none of which are
incorporated by reference in this AD; have
not been done: Perform a detailed inspection
of the ball screw assembly for integrity of the
primary and secondary load path, and do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330–27–
3102, Revision 08, dated December 6, 2007
(for Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340–27–4107,
Revision 08, dated December 6, 2007 (for
Model A340 series airplanes); except as
required by paragraph (m) of this AD. Do all
applicable corrective actions before further
flight.
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
(l) Certain Airplanes Excluded From
Paragraphs (k) and (n) of This AD
This paragraph specifies the airplanes
excluded from the actions required by
paragraphs (k) and (n) of this AD.
(1) Airplanes on which the actions
specified in Airbus Modifications 52269,
56056, and 55780 have been done in
production.
(2) Model A330 series airplanes on which
Airbus Mandatory Service Bulletin A330–27–
3137, dated March 20, 2007, Revision 01,
dated December 6, 2007, or Revision 02,
dated January 18, 2010; and Airbus
Mandatory Service Bulletin A330–92–3046,
Revision 04, dated July 16, 2010, or Revision
05, dated November 7, 2011; none of which
are incorporated by reference in this AD;
have been done in service.
(3) Model A340–200 and –300 series
airplanes on which the actions specified in
Airbus Mandatory Service Bulletin A340–27–
4136, dated March 20, 2007, Revision 01,
dated December 6, 2007, or Revision 02,
dated February 24, 2010; and Airbus
Mandatory Service Bulletin A340–92–4056,
Revision 03, dated July 16, 2010; have been
done in service.
(m) Service Information Exception
Where Airbus Mandatory Service Bulletin
A330–27–3102, Revision 08, dated December
6, 2007 (for Model A330 series airplanes); or
Airbus Mandatory Service Bulletin A340–27–
4107, Revision 08, dated December 6, 2007
(for Model A340 series airplanes); specify
contacting Airbus for a damage assessment,
this AD requires contacting the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent); for required actions before
further flight, and doing the specified actions
within the times given.
tkelley on DSK3SPTVN1PROD with RULES
(n) New Actions for Electronic Centralized
Aircraft Monitor (ECAM) Fault Messages
For airplanes other than those identified in
paragraphs (l)(1), (l)(2), and (l)(3) of this AD,
if one of the ‘‘PRIM X PITCH FAULT’’ or
‘‘STAB CTL FAULT’’ messages is displayed
on the ECAM associated with the ‘‘PITCH
TRIM ACTR (1CS)’’ maintenance message, do
the applicable detailed inspection and all
applicable corrective actions specified in
paragraph (k)(1) or (k)(2) of this AD, as
applicable to airplane configuration, before
further flight after the message is displayed
on the ECAM.
(o) New Optional Method of Compliance
For airplanes having THSA P/N 47147–
500, 47147–700, 47172–300, 47172–500, or
47172–510, accomplishing the repetitive
actions specified in paragraph (o)(1) or (o)(2)
of this AD, as applicable, is acceptable for
compliance with the corresponding actions
specified in paragraph (k)(1) or (k)(2) of this
AD, as applicable.
(1) For Model A330 series airplanes: The
repetitive actions specified in paragraphs
(o)(1)(i) through (o)(1)(viii) of this AD.
(i) Task 274400–00001–1–E of Airbus A330
ALS Part 4—Ageing Systems Maintenance,
Revision 02, dated December 16, 2009.
(ii) Task 274400–00001–1–E of Airbus
A330 ALS Part 4—Ageing Systems
VerDate Mar<15>2010
17:14 Aug 05, 2013
Jkt 229001
Maintenance, Revision 03, dated September
9, 2011.
(iii) Task 274400–00001–2–E of Airbus
A330 ALS Part 4—Ageing Systems
Maintenance, Revision 02, dated December
16, 2009.
(iv) Task 274400–00001–2–E of Airbus
A330 ALS Part 4—Ageing Systems
Maintenance, Revision 03, dated September
9, 2011.
(v) Task 274400–00001–3–E of Airbus
A330 ALS Part 4—Ageing Systems
Maintenance, Revision 02, dated December
16, 2009.
(vi) Task 274400–00001–3–E of Airbus
A330 ALS Part 4—Ageing Systems
Maintenance, Revision 03, dated September
9, 2011.
(vii) Task 274400–00001–4–E of Airbus
A330 ALS Part 4—Ageing Systems
Maintenance, Revision 02, dated December
16, 2009.
(viii) Task 274400–00001–4–E of Airbus
A330 ALS Part 4—Ageing Systems
Maintenance, Revision 03, dated September
9, 2011.
(2) For Model A340–200 and –300 series
airplanes: The repetitive actions specified in
paragraphs (o)(2)(i) through (o)(2)(viii) of this
AD.
(i) Task 274400–00001–1–E of Airbus A340
ALS Part 4—Ageing Systems Maintenance,
Revision 01, dated December 15, 2009.
(ii) Task 274400–00001–1–E of Airbus
A340 ALS Part 4—Ageing Systems
Maintenance, Revision 02, dated October 12,
2011.
(iii) Task 274400–00001–2–E of Airbus
A340 ALS Part 4—Ageing Systems
Maintenance, Revision 01, dated December
15, 2009.
(iv) Task 274400–00001–2–E of Airbus
A340 ALS Part 4—Ageing Systems
Maintenance, Revision 02, dated October 12,
2011.
(v) Task 274400–00001–3–E of Airbus
A340 ALS Part 4—Ageing Systems
Maintenance, Revision 01, dated December
15, 2009.
(vi) Task 274400–00001–3–E of Airbus
A340 ALS Part 4—Ageing Systems
Maintenance, Revision 02, dated October 12,
2011.
(vii) Task 274400–00001–4–E of Airbus
A340 ALS Part 4—Ageing Systems
Maintenance, Revision 01, dated December
15, 2009.
(viii) Task 274400–00001–4–E of Airbus
A340 ALS Part 4—Ageing Systems
Maintenance, Revision 02, dated October 12,
2011.
(p) New Credit for Previous Actions
(1) For Model A300 series airplanes: This
paragraph provides credit for the actions
specified in paragraph (j) of this AD, if those
actions were performed before the effective
date of this AD using Task 27.40.00/02,
Lubrication of THS Actuator Ball Screw Nut,
of Airbus A330 MRBR, Revision 11, dated
June 18, 2008 (which is not incorporated by
reference in this AD).
(2) For Model A340 series airplanes: This
paragraph provides credit for the actions
specified in paragraph (j) of this AD, if those
actions were performed before the effective
PO 00000
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Fmt 4700
Sfmt 4700
date of this AD using Task 27.40.00/02,
Lubrication of THS Actuator Ball Screw Nut,
of Airbus A340 MRBR, Revision 11, dated
June 18, 2008 (which is not incorporated by
reference in this AD).
(3) For Model A330 series airplanes: This
paragraph provides credit for the inspections
and corrective actions required by paragraph
(k) of this AD, if those actions were
performed before the effective date of this AD
using the service information specified in
paragraphs (p)(3)(i) through (p)(3)(vi) of this
AD (which are not incorporated by reference
in this AD).
(i) Airbus Service Bulletin A330–27–3102,
Revision 02, dated November 7, 2002.
(ii) Airbus Service Bulletin A330–27–3102,
Revision 03, dated June 20, 2003.
(iii) Airbus Service Bulletin A330–27–
3102, Revision 04, dated December 8, 2003.
(iv) Airbus Mandatory Service Bulletin
A330–27–3102, Revision 05, dated July 7,
2004.
(v) Airbus Mandatory Service Bulletin
A330–27–3102, Revision 06, dated December
16, 2005.
(vi) Airbus Mandatory Service Bulletin
A330–27–3102, Revision 07, dated March 16,
2007.
(4) For Model A340 series airplanes: This
paragraph provides credit for the inspections
and corrective actions required by paragraph
(k) of this AD, if those actions were
performed before the effective date of this AD
using the service information specified in
paragraphs (p)(4)(i) through (p)(4)(vi) of this
AD (which are not incorporated by reference
in this AD).
(i) Airbus Mandatory Service Bulletin
A340–27–4107, Revision 02, dated
September 23, 2002.
(ii) Airbus Service Bulletin A340–27–4107,
Revision 03, dated December 4, 2002.
(iii) Airbus Mandatory Service Bulletin
A340–27–4107, Revision 04, dated June 20,
2003.
(iv) Airbus Mandatory Service Bulletin
A340–27–4107, Revision 05, dated December
8, 2003.
(v) Airbus Mandatory Service Bulletin
A340–27–4107, Revision 06, dated December
16, 2005.
(vi) Airbus Mandatory Service Bulletin
A340–27–4107, Revision 07, dated March 16,
2007.
(q) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1138; fax (425) 227–
1149. Information may be emailed to: 9-
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ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
tkelley on DSK3SPTVN1PROD with RULES
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2010–0192
(corrected), dated October 11, 2010; and
EASA Airworthiness Directive 2010–0193
(corrected), dated October 11, 2010; for
related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the addresses specified in
paragraphs (s)(5), (s)(6), and (s)(7) of this AD.
(s) 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 the AD specifies otherwise.
(3) The following service information was
approved for IBR on September 10, 2013.
(i) Airbus Mandatory Service Bulletin
A330–27–3102, Revision 08, dated December
6, 2007.
(ii) Airbus Mandatory Service Bulletin
A340–27–4107, Revision 08, dated December
6, 2007.
(iii) Task 27.40.00/02, Lubrication of
Trimmable Horizontal Stabilizer (THS)
Actuator Ball Screw Nut, of Airbus A330
Maintenance Review Board Report (MRBR),
Revision 12, dated July 1, 2010.
(iv) Task 27.40.00/02, Lubrication of THS
Actuator Ball Screw Nut, of Airbus A340
MRBR, Revision 12, dated July 1, 2010.
(v) A330 Airworthiness Limitations
Section (ALS) Part 4—Ageing Systems
Maintenance, Revision 02, dated December
16, 2009. Only the title page and Record of
Revision of this document contain the
revision level; no other page of the document
contains this information. The title page of
this document does not contain an issue date.
(vi) Airbus A330 ALS Part 4—Ageing
Systems Maintenance, Revision 03, dated
September 9, 2011. Only the title page and
Record of Revision of this document contain
the revision level; no other page of the
document contains this information. The title
page of this document does not contain an
issue date.
(vii) Airbus A340 ALS Part 4—Ageing
Systems Maintenance, Revision 01, dated
VerDate Mar<15>2010
17:14 Aug 05, 2013
Jkt 229001
December 15, 2009. Only the title page and
Record of Revision of this document contains
the revision level; no other page of this
document contains this information. The title
page of this document does not contain an
issue date.
(viii) Airbus A340 ALS Part 4—Ageing
Systems Maintenance, Revision 02, dated
October 12, 2011. Only the title page and
Record of Revision of this document contain
the revision level; no other page of the
document contains this information. The title
page of this document does not contain an
issue date.
(ix) Airbus A340 ALS Part 4—Ageing
Systems Maintenance, Revision 03, dated
November 15, 2012. Only the title page and
Record of Revision of this document contain
the revision level; no other page of the
document contains this information. The title
page of this document does not contain an
issue date.
(4) The following service information was
approved for IBR on May 4, 2005 (60 FR
16104, March 30, 2005).
(i) Airbus Service Bulletin A330–27–3007,
Revision 01, dated September 18, 1996.
(ii) Airbus Service Bulletin A330–27–3015,
dated June 7, 1995.
(iii) Airbus Service Bulletin A330–27–
3047, Revision 01, dated November 26, 1997.
(iv) Airbus Service Bulletin A330–27–
3050, dated November 15, 1996.
(v) Airbus Service Bulletin A330–27–3052,
Revision 03, dated December 5, 2001.
(vi) Airbus Service Bulletin A330–27–
3085, Revision 02, dated September 5, 2002.
(vii) Airbus Service Bulletin A330–27–
3093, Revision 01, dated September 5, 2002.
(viii) Airbus Service Bulletin A330–55–
3020, Revision 01, dated October 21, 1998.
(ix) Airbus Service Bulletin A340–27–
4007, dated April 7, 1994.
(x) Airbus Service Bulletin A340–27–4025,
dated June 7, 1995.
(xi) Airbus Service Bulletin A340–27–
4054, Revision 01, dated November 26, 1997.
(xii) Airbus Service Bulletin A340–27–
4057, dated November 15, 1996.
(xiii) Airbus Service Bulletin A340–27–
4059, Revision 03, dated December 5, 2001.
(xiv) Airbus Service Bulletin A340–27–
4089, Revision 02, dated September 5, 2002.
(xv) Airbus Service Bulletin A340–27–
4099, Revision 01, dated September 5, 2002.
(xvi) Airbus Service Bulletin A340–55–
4021, Revision 01, October 21, 1998.
(5) For Airbus service information
identified in this AD, contact Airbus SAS—
Airworthiness Office—EAL, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet: https://
www.airbus.com.
(6) For TRW Aeronautical Systems, SAMM
Avionique, and Lucas Aerospace service
information identified in this AD, contact
Goodrich Corporation, Actuation Systems,
Stafford Road, Fordhouses, Wolverhampton
WV10 7EH, England; telephone +44 (0) 1902
624938; fax +44 (0) 1902 788100; email
techpubs.wolverhampton@goodrich.com;
Internet https://www.goodrich.com/TechPubs.
(7) You may review copies of the service
information at the FAA, Transport Airplane
PO 00000
Frm 00017
Fmt 4700
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47543
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(8) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 21,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–18774 Filed 8–5–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0209; Directorate
Identifier 2012–NM–127–AD; Amendment
39–17514; AD 2013–14–09]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2012–14–
04 for certain Bombardier, Inc. Model
DHC–8–100, –200, and –300 series
airplanes. AD 2012–14–04 required
replacing certain parking brake
accumulators. This new AD retains this
requirement. This new AD also requires
installing restraint devices around the
parking brake accumulator end caps. We
are issuing this AD to prevent failure of
a parking brake accumulator screw cap
or end cap resulting in loss of the
number 2 hydraulic system and damage
to airplane structures, which could
adversely affect the controllability of the
airplane.
DATES: This AD becomes effective
September 10, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 10, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of August 27, 2012 (77 FR
42956, July 23, 2012).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
SUMMARY:
E:\FR\FM\06AUR1.SGM
06AUR1
]]>Agencies
[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Rules and Regulations]
[Pages 47537-47543]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18774]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1033; Directorate Identifier 2010-NM-266-AD;
Amendment 39-17504; AD 2013-13-16]
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) 2005-07-04 for
all Airbus Model A330-200 and -300 series airplanes, and Model A340-200
and -300 series airplanes. AD 2005-07-04 required repetitive
inspections to detect discrepancies of the transfer tubes and the
collar of the ball nut of the trimmable horizontal stabilizer actuator
(THSA), and corrective action if necessary; repetitive inspections for
discrepancies of the ball screw assembly, and corrective action if
necessary; 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 removes certain inspections, revises certain actions, and
adds airplanes to the applicability. This AD was prompted by several
reports of
[[Page 47538]]
disconnection of the transfer tube from the ball nut of the THSA. We
are issuing this AD to prevent degraded operation of the THSA, which
could result in reduced controllability of the airplane.
DATES: This AD becomes effective September 10, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 10,
2013.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 4,
2005 (70 FR 16104, March 30, 2005).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: 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 include an AD that would apply to the specified products.
The NPRM was published in the Federal Register on October 2, 2012 (77
FR 60075), and proposed to supersede AD 2005-07-04, Amendment 39-14028
(70 FR 16104, March 30, 2005). (AD 2005-07-04 superseded AD 2001-11-09,
Amendment 39-12252 (66 FR 31143, June 11, 2001).) The NPRM proposed to
correct an unsafe condition for the specified products. The European
Aviation Safety Agency (EASA), which is the Technical Agent for the
Member States of the European Community, has issued EASA Airworthiness
Directive 2010-0192 (corrected), dated October 11, 2010; and EASA
Airworthiness Directive 2010-0193 (corrected), dated October 11, 2010;
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for the
specified products. 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.
This condition is caused by water ingress into the ball-nut
resulting in the jamming of the ball transfer circuit when the water
freezes.
If the three (independent) ball circuits fail, then the THSA
will operate on a fail-safe nut. This nut (which operates without
balls) would then jam after several movements on the screw of the
THSA.
This degraded operation is not detectable in the cockpit by the
crew as long as the THSA does not jam and could damage the ball
screw and the fail-safe nut.
To detect this unsafe condition, [Direcci[oacute]n General de
Aviaci[oacute]n Civil] DGAC France AD F-2001-356 [and F-2001-357]
was issued to require repetitive inspections of the transfer tubes
and their collars in order to detect at an early stage any
distortion or initiation of disconnection.
Further to a new case of transfer tube disconnection, * * *
[revised DGAC ADs] required an additional repetitive greasing task
with reinforcement of the ball-nut maintenance greasing
instructions.
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 ECAM [electronic centralized aircraft monitor]. In this case a
mandatory inspection of the THSA is required before the next flight.
DGAC France AD F-2002-038 [and F-2002-037] required application
of a final fix (related to inspection and greasing task required by
DGAC France AD F-2001-356 [and F-2001-357]) for the THSA P/N 47172
by application of Airbus modification 49590/Service Bulletin (SB)
A330-27-3085 [or SB A340-27-4089]. It changes the THSA P/N from
47172 to 47172-300.
Later on, DGAC France AD F-2002-414R3 replaced the DGAC AD
France F-2001-356R2 and F-2002-038 [and DGAC France AD F2002-415R2
superseded DGAC France ADs F-2001-357R2 and F-2002-037] requiring:
--the repetitive [detailed] inspection [for discrepancies] of all
THSA P/N in service [for integrity of the primary and secondary load
path and check the Checkable Shear Pins (CSPs)], and
--the lubrication of some THSA P/N, and
--the replacement of THSA P/N 47172, 47147-400 and 47147-2XX/-3XX
[DGAC France AD F-2002-414R3 and F-2002-415R2 correspond to FAA AD
2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 2005).]
Airbus has later introduced 4 new THSA P/N (47172-500, 47172-
510, 47172-520 and 47172-530).
This [EASA] AD retains the requirements of DGAC France AD F-
2002-414R3 [and F-2002-415R2], which is superseded, and requires
repetitive inspections and lubrications of the new THSA P/N.
The repetitive inspection and lubrication requirements for THSA
P/N 47172-520 and 47172-530 shall [also] be included in the next
Airworthiness Limitation Section (ALS) Part 4 revision.
* * * * *
Corrective actions include replacing the THSA with a new THSA if
cracks, dents, or corrosion are found, or if the feeler gage has failed
at any of the four gaps. Other corrective action includes using a
method approved by the FAA or the EASA (or its delegated agent) for a
finding of metallic debris, loose nut, damaged or missing lock washers,
pins and parts, or incorrect installation of items. AD 2005-07-04,
Amendment 39-14028 (70 FR 16104, March 30, 2005), required repetitive
inspections for discrepancies. This AD requires, for certain airplanes,
repetitive inspections for the integrity of the primary and secondary
load path, and the CSPs. The unsafe condition is the degraded operation
of the THSA, which could result in reduced controllability of the
airplane. You may obtain further information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request To Use Later Document Revision
Delta Airlines (Delta) requested that paragraph (j)(2) of the NPRM
(77 FR 60075, October 2, 2012) refer to Airbus A330 Airworthiness
Limitations Section (ALS) Part 4--Ageing Systems Maintenance, Revision
03, dated September 9, 2011; instead of Revision 02, dated December 16,
2009. Delta stated that Revision 03 of that ALS specifies the 1,000
flight-hour lubrication threshold and repetitive interval that are
specified in paragraph (j)(2) of the NPRM, whereas Revision 02 of this
ALS specifies 700 flight hours for the lubrication threshold and
repetitive interval.
We agree that Airbus A330 Airworthiness Limitations Section (ALS)
Part 4--Ageing Systems Maintenance, Revision 03, dated September 9,
2011, correctly specifies the lubrication threshold and repetitive
interval. We have changed paragraph (j)(2) of this AD accordingly. In
addition, we have changed paragraph (j)(2) of this AD to reference
Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 02, dated
October 12, 2011; and Revision 03, dated November 15, 2012; for the
same reason.
Request To Change Wording
Delta requested that we change the wording in paragraph (l) of the
NPRM (77 FR 60075, October 2, 2012), which states ``For airplanes
identified in paragraph (k) of this AD.'' The commenter asked that the
wording ``identified in'' be replaced with
[[Page 47539]]
``affected by.'' The commenter provided no reason for the change.
We disagree to change the wording in paragraph (n) in this AD
(identified as paragraph (l) in the NPRM (77 FR 60075, October 2,
2012)) as requested by the commenter. However, we have moved the
content of paragraphs (k)(1), (k)(2), and (k)(3) of the NPRM to new
paragraph (l) in this AD to clarify the actions and affected airplanes.
We have also moved the content of paragraph (k)(6) of the NPRM to new
paragraph (m) of this AD, and re-identified succeeding paragraphs
accordingly. Finally, in paragraph (n) of this AD, we revised the
wording to describe the affected airplanes.
Request To Include Additional Part Number
Delta requested that we include THSA P/N 47172-520 and P/N ``47127-
530'' in paragraph (m) of the NPRM (77 FR 60075, October 2, 2012) as
applicable part numbers for Model A330 series airplanes.
We disagree to include THSA P/N 47127-530 as there is no such part
number. We infer that the commenter meant to specify THSA P/N 47172-
530. THSA P/N 47172-520 and P/N 47172-530 are not included in the MCAI.
However, all necessary tasks for those THSA part numbers are contained
in Airbus A330 Airworthiness Limitations Section (ALS) Part 4--Ageing
Systems Maintenance, Revision 03, dated September 9, 2011; and Airbus
A340 ALS Part 4--Ageing Systems Maintenance, Revision 02, dated October
12, 2011, and Revision 03, dated November 15, 2012. The FAA NPRMs to
mandate these ALS Part 4 documents are pending at this time. Therefore,
we have not changed this AD in this regard.
Request To Consider Another EASA AD
Corinne Dayde stated that she ``Cannot see how EASA 2012-0061 is
considered.''
We are considering addressing EASA AD 2012-0061R1, dated November
30, 2012, in a separate FAA AD. We have not changed this AD in this
regard.
Conclusion
We reviewed the available data, including the comments received,
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 changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 60075, October 2, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 60075, October 2, 2012).
Costs of Compliance
We estimate that this AD will affect about 33 products of U.S.
registry.
The actions that are required by AD 2005-07-04, Amendment 39-14028
(70 FR 16104, March 30, 2005), and retained in this AD take up to 36
work-hours per product, at an average labor rate of $85 per work-hour.
Based on these figures, the estimated cost of the retained actions is
up to $3,060 per product.
We estimate that it will take about 2 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $5,610, or $170 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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)
2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 2005), and
adding the following new AD:
2013-13-16 Airbus: Amendment 39-17504. Docket No. FAA-2012-1033;
Directorate Identifier 2010-NM-266-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective September
10, 2013.
(b) Affected ADs
This AD supersedes AD 2005-07-04, Amendment 39-14028 (70 FR
16104, March 30, 2005).
(c) Applicability
This AD applies to all Airbus Model A330-201, -202, -203, -223,
-223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes; and Model A340-
[[Page 47540]]
211, -212, -213, -311, -312, and -313 airplanes; certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 27: Flight
Controls.
(e) Reason
This AD was prompted by several reports of disconnection of the
transfer tube from the ball nut of the trimmable horizontal
stabilizer actuator (THSA). We are issuing this AD to prevent
degraded operation of the THSA, which could result in reduced
controllability of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Modification or Replacement
This paragraph restates the requirements of paragraph (g) of AD
2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 2005). Except
for Model A330-223F and -243F airplanes: Within 24 months after May
4, 2005 (the effective date of AD 2005-07-04), modify the ball nut
of each THSA by doing paragraph (g)(1) or (g)(2) of this AD, as
applicable.
(1) For THSAs having part number (P/N) 47172: Modify the ball
nut of the THSA, or replace the existing THSA with a serviceable
part having P/N 47172-300; in accordance with Airbus Service
Bulletin A330-27-3085 (for Model A330 series airplanes) or A340-27-
4089 (for Model A340-313 series airplanes), both Revision 02, both
dated September 5, 2002; as applicable.
Note 1 to paragraph (g)(1) of this AD: Airbus Service Bulletins
A330-27-3085 and A340-27-4089, both Revision 02, both dated
September 5, 2002, refer to TRW Aeronautical Systems Service
Bulletin 47172-27-03, dated October 24, 2001 (which is not
incorporated by reference in this AD), as additional guidance for
accomplishing the modification of the ball nut of the THSA.
(2) For THSAs having P/N 47147-200, -210, -213, -300, -303, -
350, or -400: Modify the ball nut of the THSA, or replace the
existing THSA with an improved part having P/N 47147-500; as
applicable; in accordance with Airbus Service Bulletin A330-27-3093
(for Model A330 series airplanes) or A340-27-4099 (for Model A340-
200 and -300 series airplanes), both Revision 01, both dated
September 5, 2002; as applicable.
Note 2 to paragraph (g)(2) of this AD: Airbus Service Bulletins
A330-27-3093 and A340-27-4099, both Revision 01, both dated
September 5, 2002, refer to TRW Aeronautical Systems Service
Bulletin 47147-27-10, dated June 27, 2002 (which is not incorporated
by reference in this AD), as additional guidance for accomplishing
the modification of the ball nut of the THSA.
(h) Retained Previous/Concurrent Requirements
This paragraph restates the requirements of paragraph (h) of AD
2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 2005).
(1) Except for Model A330-223F and -243F airplanes, prior to or
concurrently with accomplishing the requirements of paragraph (g)(2)
of this AD, do all of the actions specified in the Accomplishment
Instructions of the applicable Airbus service bulletins listed in
table 1 or 2 to paragraph (h)(1) of this AD, as applicable, in
accordance with those service bulletins.
Note 3 to paragraph (h)(1) of this AD: Airbus Service Bulletin
A330-27-3093, Revision 01, dated September 5, 2002, specifies that
the actions in Airbus Service Bulletin A330-27-3052 be accomplished
previously or concurrently. Airbus Service Bulletin A330-27-3052,
Revision 03, dated December 5, 2001, specifies that the actions in
Airbus Service Bulletins A330-27-3007, A330-27-3015, A330-27-3047,
A330-27-3050, and A330-55-3020 be accomplished previously or
concurrently.
Note 4 to paragraph (h)(1) of this AD: Airbus Service Bulletin
A340-27-4099, Revision 01, dated September 5, 2002, specifies that
the actions in Airbus Service Bulletin A340-27-4059 be accomplished
previously or concurrently. Airbus Service Bulletin A340-27-4059,
Revision 03, dated December 5, 2001, specifies that the actions in
Airbus Service Bulletins A340-27-4007, A340-27-4025, A340-27-4054,
A340-27-4057, and A340-55-4021 be accomplished previously or
concurrently.
Table 1 to Paragraph (h)(1) of This AD--Retained Previous/Concurrent Requirements for Model A330 Series Airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Additional source of guidance (not
Airbus service bulletin-- Revision Date-- Main action-- incorporated by reference in this
level-- AD)--
--------------------------------------------------------------------------------------------------------------------------------------------------------
A330[dash]27[dash]3007........ 01 September 18, 1996................... Replace rudder servo controls with Samm Avionique Service Bulletin
modified parts. SC5300-27-24-01, dated April 15,
1994.
A330[dash]27[dash]3015........ ......... June 7, 1995......................... Modify the control valve detent Lucas Aerospace Service Bulletin
and the jamming protection device 47147-27-02, Revision 1, dated
on the THSA. January 31, 1996.
A330[dash]27[dash]3047........ 01 November 26, 1997.................... Replace hydraulic motors on the Lucas Aerospace Service Bulletin
THSA with new parts. 47147-27-04, Revision 1, dated
June 20, 1997.
A330[dash]27[dash]3050........ ......... November 15, 1996.................... Replace mechanical input shaft for Lucas Aerospace Service Bulletin
THSA with modified part. 47147-27-05, dated November 8,
1996.
A330[dash]27[dash]3052........ 03 December 5, 2001..................... Replace THSA with a modified THSA. Lucas Aerospace Service Bulletin
47147-27-07, dated May 4, 1998.
A330[dash]55[dash]3020........ 01 October 21, 1998..................... Perform a general visual None.
inspection of the THSA screw jack
fitting assembly for correct
installation of a washer; and
correctly install washer as
applicable.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Table 2 to Paragraph (h)(1) of This AD--Retained Previous/Concurrent Requirements for Model A340 Series Airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Additional source of guidance (not
Airbus service bulletin-- Revision Date-- Main action-- incorporated by reference in this
level-- AD)--
--------------------------------------------------------------------------------------------------------------------------------------------------------
A340[dash]27[dash]4007........ ......... April 7, 1994........................ Replace hydraulic motors on the Lucas Aerospace Service Bulletin
THSA with new parts. 47147-27-01, dated May 4, 1998.
A340[dash]27[dash]4025........ ......... June 7, 1995......................... Modify the control valve detent Lucas Aerospace Service Bulletin
and the jamming protection device 47147-27-02, Revision 1, dated
on the THSA. January 31, 1996.
[[Page 47541]]
A340[dash]27[dash]4054........ 01 November 26, 1997.................... Replace hydraulic motors on the Lucas Aerospace Service Bulletin
THSA with new parts. 47147-27-04, Revision 1, dated
June 20, 1997.
A340[dash]27[dash]4057........ ......... November 15, 1996.................... Replace mechanical input shaft for Lucas Aerospace Service Bulletin
THSA with modified part. 47147-27-05, dated November 8,
1996.
A340[dash]27[dash]4059........ 03 December 5, 2001..................... Replace THSA with a modified THSA. Lucas Aerospace Service Bulletin
47147-27-07, dated May 4, 1998.
A340[dash]55[dash]4021........ 01 October 21, 1998..................... Perform a general visual None.
inspection of the THSA screw jack
fitting assembly for correct
installation of a washer; and
correctly install washer as
applicable.
--------------------------------------------------------------------------------------------------------------------------------------------------------
(2) For the purposes of this AD, a general visual inspection is:
A visual examination of an interior or exterior area, installation,
or assembly to detect obvious damage, failure, or irregularity. This
level of inspection is made from within touching distance unless
otherwise specified. A mirror may be necessary to ensure visual
access to all surfaces in the inspection area. This level of
inspection is made under normally available lighting conditions such
as daylight, hangar lighting, flashlight, or droplight and may
require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.
(i) Retained Credit for Previous Actions
(1) This paragraph provides credit for the requirements of
paragraph (g)(1) of this AD, if those actions were performed before
May 4, 2005 (the effective date of AD 2005-07-04, Amendment 39-14028
(70 FR 16104, March 30, 2005)), using Airbus Service Bulletin A330-
27-3085 (for Model A330 series airplanes) or A340-27-4089 (for Model
A340-313 series airplanes), both Revision 01, both dated January 23,
2002 (which are not incorporated by reference in this AD), as
applicable.
(2) This paragraph provides credit for the requirements of
paragraphs (g)(2) of this AD, if those actions were performed before
May 4, 2005 (the effective date of AD 2005-07-04, Amendment 39-14028
(70 FR 16104, March 30, 2005)), using Airbus Service Bulletin A330-
27-3093 (for Model A330 series airplanes) or A340-27-4099 (for Model
A340-200 and -300 series airplanes), both dated June 27, 2002 (which
are not incorporated by reference in this AD), as applicable.
(j) New Repetitive Greasing Procedure
(1) Within 700 flight hours after the effective date of this AD,
or within 700 flight hours after the date of the last lubrication,
whichever occurs later; and thereafter at intervals not to exceed
700 flight hours from the last lubrication of the trimmable
horizontal stabilizer (THS) actuator ball screw nut: Perform Task
27.40.00/02, Lubrication of THS Actuator Ball Screw Nut, in
accordance with Airbus A330 Maintenance Review Board Report (MRBR),
Revision 12, dated July 1, 2010 (for Model A330 series airplanes);
or Airbus A340 MRBR, Revision 12, dated July 1, 2010 (for Model A340
series airplanes); on all THSAs.
(2) For airplanes identified in paragraphs (j)(2)(i),
(j)(2)(ii), and (j)(2)(iii) of this AD, as applicable, lubrication
of the THS actuator ball screw nut performed at a threshold of 1,000
flight hours and a repetitive interval not exceeding 1,000 flight
hours, in accordance with Task 274400-00002-1-E, Lubrication of the
THSA Ball Nut, of Airbus A330 Airworthiness Limitations Section
(ALS) Part 4--Ageing Systems Maintenance, Revision 03, dated
September 9, 2011 (for Model A330 series airplanes); or 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,
or Revision 03, dated November 15, 2012 (for Model A340-200 and -300
series airplanes); is acceptable for compliance with the
requirements of paragraph (j)(1) of this AD.
(i) Airplanes on which Airbus Modifications 52269, 56056, and
55780 have been done in production.
(ii) Model A330 series airplanes on which the actions specified
in Airbus Mandatory Service Bulletin A330-27-3137, dated March 20,
2007, or Revision 01, dated December 6, 2007, or Revision 02, dated
January 18, 2010; and Airbus Mandatory Service Bulletin A330-92-
3046, Revision 04, dated July 16, 2010, or Revision 05, dated
November 7, 2011; which are not incorporated by reference in this
AD; have been done in service.
(iii) Model A340-200 and -300 series airplanes on which the
actions specified in Airbus Mandatory Service Bulletin A340-27-4136,
dated March 20, 2007, Revision 01, dated December 6, 2007, or
Revision 02, dated February 24, 2010; and Airbus Mandatory Service
Bulletin A340-92-4056, Revision 03, dated July 16, 2010; which are
not incorporated by reference in this AD; have been done in service.
(k) New Repetitive Inspections of the Ball Screw Assembly and
Corrective Actions
For airplanes other than those identified in paragraphs (l)(1),
(l)(2), and (l)(3) of this AD: Do the applicable actions specified
in paragraphs (k)(1) and (k)(2) of this AD within 700 flight hours
after the effective date of this AD, and repeat the inspection
thereafter at intervals not to exceed 700 flight hours.
(1) For airplanes on which the actions specified in Airbus
Mandatory Service Bulletin A330-27-3137, dated March 20, 2007,
Revision 01, dated December 6, 2007, or Revision 02, dated January
18, 2010 (for Model A330 series airplanes); or Airbus Mandatory
Service Bulletin A340-27-4136, dated March 20, 2007, Revision 01,
dated December 6, 2007, or Revision 02, dated February 24, 2010 (for
Model A340-200 and -300 series airplanes); none of which are
incorporated by reference in this AD; have been done: Do the
applicable detailed inspection of the ball screw assembly for
integrity of the primary and secondary load path and check the
checkable shear pins (CSP), and do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330-27-3102, Revision 08, dated
December 6, 2007 (for Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340-27-4107, Revision 08, dated December
6, 2007 (for Model A340-200 and -300 series airplanes); except as
required by paragraph (m) of this AD. Do all applicable corrective
actions before further flight.
(2) For airplanes on which the actions specified in Airbus
Mandatory Service Bulletin A330-27-3137, dated March 20, 2007,
Revision 01, dated December 6, 2007, or Revision 02, dated January
18, 2010 (for Model A330 series airplanes); or Airbus Mandatory
Service Bulletin A340-27-4136, dated March 20, 2007, Revision 01,
dated December 6, 2007, or Revision 02, dated February 24, 2010 (for
Model A340-200 and -300 series airplanes); none of which are
incorporated by reference in this AD; have not been done: Perform a
detailed inspection of the ball screw assembly for integrity of the
primary and secondary load path, and do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330-27-3102, Revision 08, dated
December 6, 2007 (for Model A330 series airplanes); or Airbus
Mandatory Service Bulletin A340-27-4107, Revision 08, dated December
6, 2007 (for Model A340 series airplanes); except as required by
paragraph (m) of this AD. Do all applicable corrective actions
before further flight.
[[Page 47542]]
(l) Certain Airplanes Excluded From Paragraphs (k) and (n) of This AD
This paragraph specifies the airplanes excluded from the actions
required by paragraphs (k) and (n) of this AD.
(1) Airplanes on which the actions specified in Airbus
Modifications 52269, 56056, and 55780 have been done in production.
(2) Model A330 series airplanes on which Airbus Mandatory
Service Bulletin A330-27-3137, dated March 20, 2007, Revision 01,
dated December 6, 2007, or Revision 02, dated January 18, 2010; and
Airbus Mandatory Service Bulletin A330-92-3046, Revision 04, dated
July 16, 2010, or Revision 05, dated November 7, 2011; none of which
are incorporated by reference in this AD; have been done in service.
(3) Model A340-200 and -300 series airplanes on which the
actions specified in Airbus Mandatory Service Bulletin A340-27-4136,
dated March 20, 2007, Revision 01, dated December 6, 2007, or
Revision 02, dated February 24, 2010; and Airbus Mandatory Service
Bulletin A340-92-4056, Revision 03, dated July 16, 2010; have been
done in service.
(m) Service Information Exception
Where Airbus Mandatory Service Bulletin A330-27-3102, Revision
08, dated December 6, 2007 (for Model A330 series airplanes); or
Airbus Mandatory Service Bulletin A340-27-4107, Revision 08, dated
December 6, 2007 (for Model A340 series airplanes); specify
contacting Airbus for a damage assessment, this AD requires
contacting the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA) (or its delegated agent); for required actions before further
flight, and doing the specified actions within the times given.
(n) New Actions for Electronic Centralized Aircraft Monitor (ECAM)
Fault Messages
For airplanes other than those identified in paragraphs (l)(1),
(l)(2), and (l)(3) of this AD, if one of the ``PRIM X PITCH FAULT''
or ``STAB CTL FAULT'' messages is displayed on the ECAM associated
with the ``PITCH TRIM ACTR (1CS)'' maintenance message, do the
applicable detailed inspection and all applicable corrective actions
specified in paragraph (k)(1) or (k)(2) of this AD, as applicable to
airplane configuration, before further flight after the message is
displayed on the ECAM.
(o) New Optional Method of Compliance
For airplanes having THSA P/N 47147-500, 47147-700, 47172-300,
47172-500, or 47172-510, accomplishing the repetitive actions
specified in paragraph (o)(1) or (o)(2) of this AD, as applicable,
is acceptable for compliance with the corresponding actions
specified in paragraph (k)(1) or (k)(2) of this AD, as applicable.
(1) For Model A330 series airplanes: The repetitive actions
specified in paragraphs (o)(1)(i) through (o)(1)(viii) of this AD.
(i) Task 274400-00001-1-E of Airbus A330 ALS Part 4--Ageing
Systems Maintenance, Revision 02, dated December 16, 2009.
(ii) Task 274400-00001-1-E of Airbus A330 ALS Part 4--Ageing
Systems Maintenance, Revision 03, dated September 9, 2011.
(iii) Task 274400-00001-2-E of Airbus A330 ALS Part 4--Ageing
Systems Maintenance, Revision 02, dated December 16, 2009.
(iv) Task 274400-00001-2-E of Airbus A330 ALS Part 4--Ageing
Systems Maintenance, Revision 03, dated September 9, 2011.
(v) Task 274400-00001-3-E of Airbus A330 ALS Part 4--Ageing
Systems Maintenance, Revision 02, dated December 16, 2009.
(vi) Task 274400-00001-3-E of Airbus A330 ALS Part 4--Ageing
Systems Maintenance, Revision 03, dated September 9, 2011.
(vii) Task 274400-00001-4-E of Airbus A330 ALS Part 4--Ageing
Systems Maintenance, Revision 02, dated December 16, 2009.
(viii) Task 274400-00001-4-E of Airbus A330 ALS Part 4--Ageing
Systems Maintenance, Revision 03, dated September 9, 2011.
(2) For Model A340-200 and -300 series airplanes: The repetitive
actions specified in paragraphs (o)(2)(i) through (o)(2)(viii) of
this AD.
(i) Task 274400-00001-1-E of Airbus A340 ALS Part 4--Ageing
Systems Maintenance, Revision 01, dated December 15, 2009.
(ii) Task 274400-00001-1-E of Airbus A340 ALS Part 4--Ageing
Systems Maintenance, Revision 02, dated October 12, 2011.
(iii) Task 274400-00001-2-E of Airbus A340 ALS Part 4--Ageing
Systems Maintenance, Revision 01, dated December 15, 2009.
(iv) Task 274400-00001-2-E of Airbus A340 ALS Part 4--Ageing
Systems Maintenance, Revision 02, dated October 12, 2011.
(v) Task 274400-00001-3-E of Airbus A340 ALS Part 4--Ageing
Systems Maintenance, Revision 01, dated December 15, 2009.
(vi) Task 274400-00001-3-E of Airbus A340 ALS Part 4--Ageing
Systems Maintenance, Revision 02, dated October 12, 2011.
(vii) Task 274400-00001-4-E of Airbus A340 ALS Part 4--Ageing
Systems Maintenance, Revision 01, dated December 15, 2009.
(viii) Task 274400-00001-4-E of Airbus A340 ALS Part 4--Ageing
Systems Maintenance, Revision 02, dated October 12, 2011.
(p) New Credit for Previous Actions
(1) For Model A300 series airplanes: This paragraph provides
credit for the actions specified in paragraph (j) of this AD, if
those actions were performed before the effective date of this AD
using Task 27.40.00/02, Lubrication of THS Actuator Ball Screw Nut,
of Airbus A330 MRBR, Revision 11, dated June 18, 2008 (which is not
incorporated by reference in this AD).
(2) For Model A340 series airplanes: This paragraph provides
credit for the actions specified in paragraph (j) of this AD, if
those actions were performed before the effective date of this AD
using Task 27.40.00/02, Lubrication of THS Actuator Ball Screw Nut,
of Airbus A340 MRBR, Revision 11, dated June 18, 2008 (which is not
incorporated by reference in this AD).
(3) For Model A330 series airplanes: This paragraph provides
credit for the inspections and corrective actions required by
paragraph (k) of this AD, if those actions were performed before the
effective date of this AD using the service information specified in
paragraphs (p)(3)(i) through (p)(3)(vi) of this AD (which are not
incorporated by reference in this AD).
(i) Airbus Service Bulletin A330-27-3102, Revision 02, dated
November 7, 2002.
(ii) Airbus Service Bulletin A330-27-3102, Revision 03, dated
June 20, 2003.
(iii) Airbus Service Bulletin A330-27-3102, Revision 04, dated
December 8, 2003.
(iv) Airbus Mandatory Service Bulletin A330-27-3102, Revision
05, dated July 7, 2004.
(v) Airbus Mandatory Service Bulletin A330-27-3102, Revision 06,
dated December 16, 2005.
(vi) Airbus Mandatory Service Bulletin A330-27-3102, Revision
07, dated March 16, 2007.
(4) For Model A340 series airplanes: This paragraph provides
credit for the inspections and corrective actions required by
paragraph (k) of this AD, if those actions were performed before the
effective date of this AD using the service information specified in
paragraphs (p)(4)(i) through (p)(4)(vi) of this AD (which are not
incorporated by reference in this AD).
(i) Airbus Mandatory Service Bulletin A340-27-4107, Revision 02,
dated September 23, 2002.
(ii) Airbus Service Bulletin A340-27-4107, Revision 03, dated
December 4, 2002.
(iii) Airbus Mandatory Service Bulletin A340-27-4107, Revision
04, dated June 20, 2003.
(iv) Airbus Mandatory Service Bulletin A340-27-4107, Revision
05, dated December 8, 2003.
(v) Airbus Mandatory Service Bulletin A340-27-4107, Revision 06,
dated December 16, 2005.
(vi) Airbus Mandatory Service Bulletin A340-27-4107, Revision
07, dated March 16, 2007.
(q) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone (425) 227-1138; fax (425) 227-1149.
Information may be emailed to: 9-
[[Page 47543]]
ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC,
notify your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding district office. The AMOC approval letter
must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(r) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2010-0192 (corrected), dated
October 11, 2010; and EASA Airworthiness Directive 2010-0193
(corrected), dated October 11, 2010; for related information. This
MCAI may be found in the AD docket on the Internet at https://www.regulations.gov.
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at the addresses specified
in paragraphs (s)(5), (s)(6), and (s)(7) of this AD.
(s) 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 the AD specifies otherwise.
(3) The following service information was approved for IBR on
September 10, 2013.
(i) Airbus Mandatory Service Bulletin A330-27-3102, Revision 08,
dated December 6, 2007.
(ii) Airbus Mandatory Service Bulletin A340-27-4107, Revision
08, dated December 6, 2007.
(iii) Task 27.40.00/02, Lubrication of Trimmable Horizontal
Stabilizer (THS) Actuator Ball Screw Nut, of Airbus A330 Maintenance
Review Board Report (MRBR), Revision 12, dated July 1, 2010.
(iv) Task 27.40.00/02, Lubrication of THS Actuator Ball Screw
Nut, of Airbus A340 MRBR, Revision 12, dated July 1, 2010.
(v) A330 Airworthiness Limitations Section (ALS) Part 4--Ageing
Systems Maintenance, Revision 02, dated December 16, 2009. Only the
title page and Record of Revision of this document contain the
revision level; no other page of the document contains this
information. The title page of this document does not contain an
issue date.
(vi) Airbus A330 ALS Part 4--Ageing Systems Maintenance,
Revision 03, dated September 9, 2011. Only the title page and Record
of Revision of this document contain the revision level; no other
page of the document contains this information. The title page of
this document does not contain an issue date.
(vii) Airbus A340 ALS Part 4--Ageing Systems Maintenance,
Revision 01, dated December 15, 2009. Only the title page and Record
of Revision of this document contains the revision level; no other
page of this document contains this information. The title page of
this document does not contain an issue date.
(viii) Airbus A340 ALS Part 4--Ageing Systems Maintenance,
Revision 02, dated October 12, 2011. Only the title page and Record
of Revision of this document contain the revision level; no other
page of the document contains this information. The title page of
this document does not contain an issue date.
(ix) Airbus A340 ALS Part 4--Ageing Systems Maintenance,
Revision 03, dated November 15, 2012. Only the title page and Record
of Revision of this document contain the revision level; no other
page of the document contains this information. The title page of
this document does not contain an issue date.
(4) The following service information was approved for IBR on
May 4, 2005 (60 FR 16104, March 30, 2005).
(i) Airbus Service Bulletin A330-27-3007, Revision 01, dated
September 18, 1996.
(ii) Airbus Service Bulletin A330-27-3015, dated June 7, 1995.
(iii) Airbus Service Bulletin A330-27-3047, Revision 01, dated
November 26, 1997.
(iv) Airbus Service Bulletin A330-27-3050, dated November 15,
1996.
(v) Airbus Service Bulletin A330-27-3052, Revision 03, dated
December 5, 2001.
(vi) Airbus Service Bulletin A330-27-3085, Revision 02, dated
September 5, 2002.
(vii) Airbus Service Bulletin A330-27-3093, Revision 01, dated
September 5, 2002.
(viii) Airbus Service Bulletin A330-55-3020, Revision 01, dated
October 21, 1998.
(ix) Airbus Service Bulletin A340-27-4007, dated April 7, 1994.
(x) Airbus Service Bulletin A340-27-4025, dated June 7, 1995.
(xi) Airbus Service Bulletin A340-27-4054, Revision 01, dated
November 26, 1997.
(xii) Airbus Service Bulletin A340-27-4057, dated November 15,
1996.
(xiii) Airbus Service Bulletin A340-27-4059, Revision 03, dated
December 5, 2001.
(xiv) Airbus Service Bulletin A340-27-4089, Revision 02, dated
September 5, 2002.
(xv) Airbus Service Bulletin A340-27-4099, Revision 01, dated
September 5, 2002.
(xvi) Airbus Service Bulletin A340-55-4021, Revision 01, October
21, 1998.
(5) For Airbus service information identified in this AD,
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet: https://www.airbus.com.
(6) For TRW Aeronautical Systems, SAMM Avionique, and Lucas
Aerospace service information identified in this AD, contact
Goodrich Corporation, Actuation Systems, Stafford Road, Fordhouses,
Wolverhampton WV10 7EH, England; telephone +44 (0) 1902 624938; fax
+44 (0) 1902 788100; email techpubs.wolverhampton@goodrich.com;
Internet https://www.goodrich.com/TechPubs.
(7) You may review copies of the 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.
(8) 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 21, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18774 Filed 8-5-13; 8:45 am]
BILLING CODE 4910-13-P
