Airworthiness Directives; Airbus Model A310 Series Airplanes and Model A300-600 Series Airplanes, 12228-12233 [E9-5969]
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Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
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/
code_of_federal_regulations/
ibr_locations.html.
TABLE 4—SERVICE BULLETINS INCORPORATED BY REFERENCE
Bombardier Service Bulletin—
Revision—
Dated—
600–0734 ........................................................................................
601–0585 ........................................................................................
604–30–003 ....................................................................................
Original .......................................................................
Original .......................................................................
01 ...............................................................................
November 30, 2006.
November 30, 2006.
January 21, 2008.
TABLE 5—TEMPORARY REVISIONS INCORPORATED BY REFERENCE
Canadair TR—
Dated—
To the—
600/23 .............................................
600–1/19 .........................................
601/14 .............................................
601/15 .............................................
601/19 .............................................
601/26 .............................................
601/27 .............................................
601/27 .............................................
604/20 .............................................
August 16, 2006 ............................
August 16, 2006 ............................
August 16, 2006 ............................
August 16, 2006 ............................
August 16, 2006 ............................
August 16, 2006 ............................
August 16, 2006 ............................
August 16, 2006 ............................
April 17, 2006 ................................
Canadair
Canadair
Canadair
Canadair
Canadair
Canadair
Canadair
Canadair
Canadair
Issued in Renton, Washington, on February
27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–5968 Filed 3–23–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0018; Directorate
Identifier 2007–NM–145–AD; Amendment
39–15842; AD 2009–06–06]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes and Model
A300–600 Series Airplanes
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AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: This airworthiness directive
(AD) supersedes two existing ADs. One
AD applies to certain Airbus Model
A310–200 and –300 series airplanes.
That AD currently requires repetitive
inspections for cracking of the flap
transmission shafts, and replacement of
the transmission shafts if necessary.
That AD also provides an optional
terminating action for the repetitive
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Challenger
Challenger
Challenger
Challenger
Challenger
Challenger
Challenger
Challenger
Challenger
inspections. The other existing AD
applies to all Airbus Model A300 B4–
600, B4–600R, and F4–600R series
airplanes, and Model C4–605R Variant F
airplanes (collectively called A300–600
series airplanes); and Model A310–200
and –300 series airplanes. That AD
currently requires a one-time inspection
of the trimmable horizontal stabilizer
actuator (THSA), corrective actions if
necessary, and follow-on repetitive
tasks. This new AD also requires
revising the Airworthiness Limitations
Section of the Instructions for
Continued Airworthiness to incorporate
new limitations and maintenance tasks
for aging systems maintenance. This AD
results from the manufacturer’s
determination that life limitations and
maintenance tasks are necessary to
ensure continued operational safety of
the affected airplanes. We are issuing
this AD to prevent reduced structural
integrity of these airplanes due to the
failure of system components.
DATES: This AD becomes effective April
28, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 28, 2009.
On August 29, 2006 (71 FR 42021,
July 25, 2006), the Director of the
Federal Register approved the
incorporation by reference of Airbus
Service Bulletin A300–27–6044,
Revision 04, dated September 10, 2001;
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Model
Model
Model
Model
Model
Model
Model
Model
Model
CL–600–1A11 AFM.
CL–600–1A11 AFM (Winglets).
CL–600–2A12 AFM, PSP 601–1B–1.
CL–600–2A12 AFM, PSP 601–1A–1.
CL–600–2A12 AFM, PSP 601–1B.
CL–600–2B16 AFM, PSP 601A–1.
CL–600–2A12 AFM.
CL–600–2B16 AFM, PSP 601A–1–1.
CL–604 AFM, PSP 604–1.
and Airbus Service Bulletin A310–27–
2089, Revision 02, dated June 28, 2001.
On June 20, 2006 (71 FR 28254, May
16, 2006), the Director of the Federal
Register approved the incorporation by
reference of Airbus Service Bulletin
A310–27–2092, Revision 02, dated April
11, 2005; and Airbus Service Bulletin
A310–27–2095, dated March 29, 2000.
ADDRESSES: For Airbus service
information identified in this AD,
contact Airbus SAS–EAW
(Airworthiness Office), 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; e-mail:
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. For
TRW Aeronautical Systems service
information identified in this AD,
`
´
contact TRW Systemes Aeronautiques
Civils SAS, Product Support
Department, 7–9 Avenue de l’Eguillette,
Saint Ouen l’Aumone BP 7186, 95056
Cergy-Pontoise Cedex France, telephone
+33 1 34 32 63 00; fax +33 1 34 32 63
10.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
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Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Thomas Stafford, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1622; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that supersedes two existing ADs:
AD 2006–10–11, amendment 39–14595
(71 FR 28254, May 16, 2006); and AD
2006–15–10, amendment 39–14690 (71
FR 42021, July 25, 2006). AD 2006–10–
11 applies to certain Airbus Model
A310–200 and –300 series airplanes and
requires repetitive inspections for
cracking of the flap transmission shafts,
12229
and replacing the transmission shafts if
necessary. That existing AD also
provides an optional terminating action
for the repetitive inspections. AD 2006–
15–10 applies to all Airbus Model A310
and A300–600 series airplanes and
requires a one-time inspection of the
trimmable horizontal stabilizer actuator
(THSA), corrective actions if necessary,
and follow-on repetitive tasks.
That supplemental NPRM was
published in the Federal Register on
September 26, 2008 (73 FR 55781). That
supplemental NPRM proposed to
continue to require the actions required
by the two existing ADs. That
supplemental NPRM also proposed to
require revising the Airworthiness
Limitations Section of the Instructions
for Continued Airworthiness to
incorporate new limitations and
maintenance tasks for aging systems
maintenance. In addition, that
supplemental NPRM proposed to revise
the original NPRM by reducing the
initial compliance times.
development of this AD. No comments
have been received on the supplemental
NPRM or on the determination of the
cost to the public.
Comments
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
We provided the public the
opportunity to participate in the
Explanation of Changes
We have removed the ‘‘Service
Bulletin References’’ paragraph in the
‘‘RESTATEMENT OF REQUIREMENTS
OF AD 2006–15–10’’ section of this AD.
Instead, we refer to the required service
documents in the individual paragraphs
of this AD.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the changes
described previously. We also
determined that these changes will not
increase the economic burden on any
operator or increase the scope of the AD.
Costs of Compliance
ESTIMATED COSTS
Action
Work hours
Inspection (required by AD
2006–10–11).
Inspection (required by AD
2006–15–10).
Repetitive follow-on tasks (required by AD 2006–15–10).
ALS revision (new action) .........
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Number
of U.S.registered
airplanes
Fleet cost
$80
$80 per inspection cycle ...........
59
3
80
$240 ..........................................
213
$51,120.
12
80
$960 per inspection cycle .........
213
$204,480 per inspection cycle.
1
80
$80 ............................................
213
$17,040.
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
01:02 Mar 24, 2009
Cost per airplane
1
Authority for This Rulemaking
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Average
labor rate
per hour
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products identified in this rulemaking
action.
Regulatory Findings
We have 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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
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$4,720 per inspection cycle.
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.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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:
■
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Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations
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 Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14595 (71
FR 28254, May 16, 2006), and
amendment 39–14690 (71 FR 42021,
July 25, 2006), and by adding the
following new airworthiness directive
(AD):
■
2009–06–06 Airbus: Amendment 39–15842.
Docket No. FAA–2008–0018; Directorate
Identifier 2007–NM–145–AD.
Effective Date
(a) This AD becomes effective April 28,
2009.
Affected ADs
(b) This AD supersedes AD 2006–10–11
and AD 2006–15–10.
Applicability
(c) This AD applies to all Airbus Model
A310 series airplanes; and Model A300–600
series airplanes; certificated in any category.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance according
to paragraph (q) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued operational safety of the airplane.
Unsafe Condition
(d) This AD results from the
manufacturer’s determination that life
limitations and maintenance tasks are
necessary to ensure continued operational
safety of the affected airplanes. We are
issuing this AD to prevent reduced structural
integrity of these airplanes due to the failure
of system components.
Compliance
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(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006–
10–11
Inspection and Corrective Action
(f) For Airbus Model A310–203, –204,
–221, –222, –304, –322, –324, and –325
airplanes, except for airplanes on which
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Airbus Modification 12247 has been
embodied in production: At the earlier of the
compliance times specified in paragraph
(f)(1) or (f)(2) of this AD, perform a detailed
inspection for stress corrosion cracking of the
flight transmission shafts located between the
power control unit (PCU) and the torque
limiters in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–27–2092, Revision 02,
dated April 11, 2005. Thereafter, repeat the
inspections as required by paragraph (g) of
this AD. Before further flight, replace any
cracked transmission shaft discovered during
any inspection required by this AD with a
new or reconditioned shaft, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A310–27–2095,
dated March 29, 2000. Doing an inspection
in accordance with paragraph (n) or (o) of
this AD terminates the requirements of this
paragraph.
(1) Within 2,000 flight hours after the last
flap asymmetry protection test performed in
accordance with Airbus A310 Maintenance
Planning Document (MPD) Task 275600–01–
1.
(2) Within 8,000 flight cycles after the last
flap asymmetry protection test performed in
accordance with Airbus A310 MPD Task
275600–02–1 or 800 flight cycles after June
20, 2006 (the effective date of AD 2006–10–
11), whichever comes later.
Note 2: Airbus Service Bulletin A310–27–
2092, Revision 02, dated April 11, 2005,
refers to Lucas Liebherr Service Bulletin
551A–27–624, Revision 1, dated August 18,
2000, as a source of service information for
accomplishing the inspections.
Note 3: Airbus Service Bulletin A310–27–
2092, Revision 02, dated April 11, 2005,
refers to Airbus Service Bulletin A310–27–
2095, dated March 29, 2000, as a source of
information for replacing the flap
transmission shafts.
Note 4: Airbus Service Bulletin A310–27–
2095, dated March 29, 2000, refers to Lucas
Liebherr Service Bulletin 551A–27–M551–
05, dated January 12, 2000, as an additional
source of information for replacing the flap
transmission shafts.
Repetitive Inspections
(g) Repeat the inspection required by
paragraph (f) of this AD at the applicable
times specified in paragraphs (g)(1), (g)(2),
and (g)(3) of this AD. Doing an inspection in
accordance with paragraph (n) or (o) of this
AD terminates the requirements of this
paragraph.
(1) Before further flight after any
occurrence of jamming of the flap
transmission system.
(2) At intervals not to exceed 2,000 flight
hours after each flap asymmetry protection
test performed in accordance with Airbus
A310 MPD Task 275600–01–1.
(3) At intervals not to exceed 8,000 flight
cycles after each flap asymmetry protection
test performed in accordance with Airbus
A310 MPD Task 275600–02–1.
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Optional Terminating Action
(h) Replacing any flap transmission shaft
with a new or reconditioned transmission
shaft in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–27–2095, dated March
29, 2000, ends the inspections required by
paragraphs (f) and (g) of this AD for that
transmission shaft only.
Actions Performed Using Previously Issued
Service Information
(i) Actions performed in accordance with
Airbus Service Bulletin A310–27–2092,
dated April 9, 1999; or Revision 01, dated
December 11, 2001; are considered
acceptable for compliance with the
corresponding requirements of paragraphs (f)
and (g) of this AD.
No Reporting
(j) Although Airbus Service Bulletin A310–
27–2092, Revision 02, dated April 11, 2005,
specifies to submit certain information to the
manufacturer, this AD does not include that
requirement.
Restatement of Requirements of AD 2006–
15–10
Inspection
(k) At the applicable time specified in
paragraph (k)(1) or (k)(2) of this AD, do a
detailed inspection of specified components
of the trimmable horizontal stabilizer
actuator (THSA) in accordance with
paragraph 1.E.(2)(a) and the Accomplishment
Instructions of the applicable service bulletin
as identified in Table 1 of this AD. Repair
any discrepancy before further flight in
accordance with TRW Aeronautical Systems
Horizontal Stabilizer Actuator 47142 Series
Component Maintenance Manual with
Illustrated Parts List 27–44–13, Revision 6,
dated September 14, 2001; or a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, or the European Aviation
Safety Agency (EASA) (or its delegated
agent). Doing an inspection in accordance
with paragraph (n) or (o) of this AD
terminates the requirements of this
paragraph.
(1) If the flight hours accumulated on the
THSA can be positively determined: Inspect
at the earlier of:
(i) Before the accumulation of 47,000 total
flight hours on the THSA, or within 600
flight hours after August 29, 2006 (the
effective date of AD 2006–15–10), whichever
occurs later.
(ii) Within 25 years since the THSA was
new or within 600 flight hours after August
29, 2006, whichever occurs later.
(2) If the flight hours accumulated on the
THSA cannot be positively determined:
Inspect before the accumulation of 47,000
total flight hours on the airplane, or within
600 flight hours after August 29, 2006,
whichever occurs later.
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12231
TABLE 1—SERVICE BULLETINS FOR THE REQUIREMENTS OF PARAGRAPH (k) OF THIS AD
Approved Airbus Service Bulletin version
for actions done before the effective date
of this AD
Required Airbus Service Bulletin
Airbus Service Bulletin A300–27–6044, Revision 04, dated September 10, 2001; or Airbus Mandatory Service Bulletin A300–27–
6044, Revision 05, dated August 29, 2006.
Airbus Service Bulletin A310–27–2089, Revision 02, dated June 28, 2001; or Airbus
Mandatory Service Bulletin A310–27–2089,
Revision 03, dated August 29, 2006.
A300–27–6044, Revision 02, dated August
26, 2000; or Revision 03, dated June 28,
2001.
Note 5: The service bulletins specified in
Table 1 of this AD refer to Goodrich
Actuation Systems Service Bulletin 47142–
27–11, Revision 3, dated April 25, 2005, as
an additional source of service information
for the required actions.
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Note 6: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
...........................................................................
Follow-on Repetitive Tasks
(l) After the inspection required by
paragraph (k) of this AD: Do the repetitive
tasks in accordance with the
Accomplishment Instructions and at the
times specified in paragraph 1.E.(2)(b) of the
applicable service bulletin identified in Table
Airbus airplane model
A300 B4–601, B4–603, B4–620, and B4–622.
A300 B4–605R and B4–622R.
A300 B4–605R and B4–622R.
A300 C4–605R Variant F.
A310–203, –204, –221, and –222.
A310–304, –322, –324, and –325.
2 of this AD, except as provided by paragraph
(m) of this AD. The repetitive tasks are valid
only until the THSA operational life exceeds
65,000 flight hours, 40,000 flight cycles, or 25
years, whichever occurs first. Before the
THSA is operated beyond these extended life
goals, it must be replaced with a new or
serviceable THSA, except as required by
paragraph (m) of this AD. Doing an
inspection in accordance with paragraph (n)
or (o) of this AD terminates the requirements
of this paragraph.
TABLE 2—SERVICE BULLETINS FOR THE REQUIREMENTS OF PARAGRAPH (L) OF THIS AD
Approved Airbus Service Bulletin version
for actions done before the effective date
of this AD
Required Airbus Service Bulletin
Airbus Service Bulletin A300–27–6044, Revision 04, dated September 10, 2001; or Airbus Mandatory Service Bulletin A300–27–
6044, Revision 05, dated August 29, 2006.
Airbus Service Bulletin A310–27–2089, Revision 02, dated June 28, 2001; or Airbus
Mandatory Service Bulletin A310–27–2089,
Revision 03, dated August 29, 2006.
A300–27–6044, Revision 02, dated August
26, 2000; or Revision 03, dated June 28,
2001.
Note 7: For additional information on the
THSA life limits, refer to Airbus Operators
Information Telex (OIT) SE 999.0074/05/BB,
dated August 3, 2005.
serviceable THSA: Within 47,000 flight hours
or 25 years, whichever occurs first, after the
THSA is replaced, do the applicable tasks
specified in paragraph 1.E.(2)(a) and the
Accomplishment Instructions of the
applicable service bulletin identified in Table
3. Thereafter repeat the tasks within the
repetitive intervals specified in paragraph
THSA Replacement
(m) For any THSA, whether discrepant or
not, that is replaced with a new or
A310–27–2089, Revision 01, dated August
25, 2000.
Airbus airplane model
A300 B4–601, B4–603, B4–620, and B4–622.
A300 B4–605R and B4–622R.
A300 B4–605R and B4–622R.
A300 C4–605R Variant F.
A310–203, –204, –221, and –222.
A310–304, –322, –324, and –325.
1.E.(2)(b) of the applicable service bulletin.
Doing the corresponding tasks in accordance
with paragraph (n) or (o) of this AD
terminates the requirements of this
paragraph.
TABLE 3—SERVICE BULLETINS FOR THE REQUIREMENTS OF PARAGRAPH (m) OF THIS AD
Approved Airbus Service Bulletin version
for actions done before the effective date
of this AD
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Required Airbus Service Bulletin
Airbus Service Bulletin A300–27–6044, Revision 04, dated September 10, 2001; or Airbus Mandatory Service Bulletin A300–27–
6044, Revision 05, dated August 29, 2006.
Airbus Service Bulletin A310–27–2089, Revision 02, dated June 28, 2001; or Airbus
Mandatory Service Bulletin A310–27–2089,
Revision 03, dated August 29, 2006.
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01:02 Mar 24, 2009
Jkt 217001
A300–27–6044, Revision 02, dated August
26, 2000; or Revision 03, dated June 28,
2001.
A310–27–2089, Revision 01, dated August
25, 2000.
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Airbus airplane model
A300 B4–601, B4–603, B4–620, and B4–622.
A300 B4–605R and B4–622R.
A300 F4–605R and F4–622R.
A300 C4–605R Variant F.
A310–203, –204, –221, and –222.
A310–304, –322, –324, and –325.
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New Requirements of This AD
Revise Airworthiness Limitations Section
(ALS) To Incorporate Limitations and
Maintenance Tasks for Aging Systems
Maintenance
(n) Within 3 months after the effective date
of this AD, revise the ALS of the Instructions
for Continued Airworthiness (ICA) to
incorporate Airbus A310 ALS Part 4—Ageing
Systems Maintenance, Revision 01, dated
December 21, 2006 (for Model A310 series
airplanes); or Airbus A300–600 ALS Part 4—
Ageing Systems Maintenance, Revision 01,
dated December 21, 2006 (for Model A300–
600 series airplanes). For all tasks identified
in Airbus A310 ALS Part 4—Ageing Systems
Maintenance, Revision 01, dated December
21, 2006; and Airbus A300–600 ALS Part 4—
Ageing Systems Maintenance, Revision 01,
dated December 21, 2006; do the tasks at the
later of the times specified in paragraphs
(n)(1) and (n)(2) of this AD, as applicable,
except as provided by paragraph (o) of this
AD. The repetitive inspections must be
accomplished thereafter at the interval
specified in Airbus A310 ALS Part 4—Ageing
Systems Maintenance, Revision 01, dated
December 21, 2006; or Airbus A300–600 ALS
Part 4—Ageing Systems Maintenance,
Revision 01, dated December 21, 2006; as
applicable. Doing an inspection required by
this paragraph terminates the corresponding
inspection required by paragraph (f), (g), (k),
(l), or (m) of this AD.
(1) At the initial compliance times
(thresholds) specified in Airbus A310 ALS
Part 4—Ageing Systems Maintenance,
Revision 01, dated December 21, 2006; or
Airbus A300–600 ALS Part 4—Ageing
Systems Maintenance, Revision 01, dated
December 21, 2006; as applicable; with the
compliance times starting from the later of
the times specified in paragraphs (n)(1)(i) and
(n)(1)(ii) of this AD.
(i) Since first flight of the airplane.
(ii) Since the applicable part was new or
refurbished if the part’s life (in flight hours,
flight cycles, landings, or calendar time, as
applicable) can be conclusively determined.
(2) Within 3 months after doing the
revision of the ALS of the ICA required by
paragraph (o) of this AD.
Note 8: For additional information on the
THSA life limits, refer to Airbus OIT SE
999.0074/05/BB, dated August 3, 2005.
Note 9: For additional information on the
THSA life limits and calculation method for
unknown history of parts, refer to Airbus OIT
SE 999.0008/07/LB, dated January 16, 2007;
and Airbus Service Information Letter 05–
008, Revision 01, dated February 21, 2007.
(o) For airplanes on which any life
limitation/maintenance task has been
complied with in accordance with the
requirements of paragraph (f), (g), (k), (l), or
(m) of this AD (e.g., AD 2006–10–11 or AD
2006–15–10), the last accomplishment of
each limitation/task must be retained as a
starting point for the accomplishment of each
corresponding limitation/task interval now
introduced in Airbus A310 ALS Part 4—
Ageing Systems Maintenance, Revision 01,
dated December 21, 2006; and Airbus A300–
600 ALS Part 4—Ageing Systems
Maintenance, Revision 01, dated December
21, 2006; as applicable. Doing an inspection
required by this paragraph terminates the
corresponding inspection required by
paragraph (f), (g), (k), (l), or (m) of this AD.
(p) Except as provided by paragraph (q) of
this AD: After accomplishing the actions
specified in paragraphs (n) and (o) of this AD,
no alternative inspection, inspection
intervals, or limitations may be used.
Alternative Methods of Compliance
(AMOCs)
(q)(1) 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. Send information to
ATTN: Thomas Stafford, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 227–1622; fax (425)
227–1149. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) AMOCs approved previously in
accordance with AD 2006–10–11 are not
approved as AMOCs with this AD.
(3) AMOCs approved previously in
accordance with AD 2006–15–10 are not
approved as AMOCs with this AD.
Related Information
(r) EASA airworthiness directive 2007–
0092, dated April 10, 2007, also addresses
the subject of this AD.
Material Incorporated by Reference
(s) You must use the service information
identified in Table 4 of this AD, as
applicable, to do the actions required by this
AD, unless the AD specifies otherwise. If you
accomplish the optional actions specified by
this AD, you must use Airbus Service
Bulletin A310–27–2095, dated March 29,
2000, to perform those actions, unless the AD
specifies otherwise.
TABLE 4—MATERIAL INCORPORATED BY REFERENCE FOR THE ACTIONS REQUIRED BY THIS AD
Document
Revision
Airbus A300–600 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance ...
Airbus A310 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance ...........
Airbus Mandatory Service Bulletin A300–27–6044 ..............................................................................
Airbus Mandatory Service Bulletin A310–27–2089 ..............................................................................
Airbus Service Bulletin A300–27–6044 ................................................................................................
Airbus Service Bulletin A310–27–2089 ................................................................................................
Airbus Service Bulletin A310–27–2092 ................................................................................................
Airbus Service Bulletin A310–27–2095 ................................................................................................
TRW Aeronautical Systems Horizontal Stabilizer Actuator 47142 Series Component Maintenance
Manual with Illustrated Parts List 27–44–13.
01 ................
01 ................
05 ................
03 ................
04 ................
02 ................
02 ................
Original ........
6 ..................
(TRW Aeronautical Systems Horizontal
Stabilizer Actuator 47142 Series Component
Maintenance Manual with Illustrated Parts
List 27–44–13 contains the following
discrepancies: The revision level of the
document is only specified on the Letter of
Transmittal; the Letter of Transmittal is not
specified in the List of Effective Pages; and
the List of Effective Pages refers to page 748a
as 748b.)
Date
December 21, 2006.
December 21, 2006.
August 29, 2006.
August 29, 2006.
September 10, 2001.
June 28, 2001.
April 11, 2005.
March 29, 2000.
September 14, 2001.
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information contained in Table 5
of this AD under 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 5—NEW MATERIAL INCORPORATED BY REFERENCE
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Document
Airbus
Airbus
Airbus
Airbus
Revision
A300–600 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance ...
A310 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance ...........
Mandatory Service Bulletin A300–27–6044 ..............................................................................
Mandatory Service Bulletin A310–27–2089 ..............................................................................
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................
................
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December 21, 2006.
December 21, 2006.
August 29, 2006.
August 29, 2006.
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Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations
TABLE 5—NEW MATERIAL INCORPORATED BY REFERENCE—Continued
Document
Revision
TRW Aeronautical Systems Horizontal Stabilizer Actuator 47142 Series Component Maintenance
Manual with Illustrated Parts List 27–44–13.
Original ........
(2) The Director of the Federal Register
previously approved the incorporation by
reference of the service information
Date
September 14, 2001.
contained in Table 6 of this AD on August
29, 2006 (71 FR 42021, July 25, 2006).
TABLE 6—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2006–15–10
Document
Revision
Airbus Service Bulletin A300–27–6044 ..............................................................................................
Airbus Service Bulletin A310–27–2089 ..............................................................................................
(3) The Director of the Federal Register
previously approved the incorporation by
reference of the service information
Date
04
02
September 10, 2001.
June 28, 2001.
contained in Table 7 of this AD on June 20,
2006 (71 FR 28254, May 16, 2006).
TABLE 7—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2006–10–11
Document
Revision
Airbus Service Bulletin A310–27–2092 ................................................................................................
Airbus Service Bulletin A310–27–2095 ................................................................................................
02 ................
Original ........
mstockstill on PROD1PC66 with RULES
(4) For Airbus service information
identified in this AD, contact Airbus SAS—
EAW (Airworthiness Office), 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(5) For TRW Aeronautical Systems service
information identified in this AD, contact
´
TRW Systemes Aeacute;ronautiques Civils
SAS, Product Support Department, 7–9
Avenue de l’Eguillette, Saint Ouen l’Aumone
BP 7186, 95056 Cergy-Pontoise Cedex
France, telephone +33 1 34 32 63 00; fax +33
1 34 32 63 10.
(6) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(7) You may also review copies of the
service information 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/code_of_federal_
regulations/ibr_locations.html.
Issued in Renton, Washington, on February
27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–5969 Filed 3–23–09; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0668; Directorate
Identifier 2008–NM–088–AD; Amendment
39–15847; AD 2009–06–11]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model ERJ 190 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
During aircraft structure fatigue tests,
cracks were found in the wing lower skin
stringers between ribs 7 and 10 on both
wings. In order to prevent fatigue cracks in
the wing lower skin stringers, which could
result in fuel leakage and reduced structural
integrity of the wing, the referred stringers
must be reworked.
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Frm 00009
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Date
April 11, 2005.
March 29, 2000.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective April
28, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 28, 2009.
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:
Kenny Kaulia, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2848; 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. That
NPRM was published in the Federal
Register on June 24, 2008 (73 FR 35597).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
E:\FR\FM\24MRR1.SGM
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]]>Agencies
[Federal Register Volume 74, Number 55 (Tuesday, March 24, 2009)]
[Rules and Regulations]
[Pages 12228-12233]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-5969]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0018; Directorate Identifier 2007-NM-145-AD;
Amendment 39-15842; AD 2009-06-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes and
Model A300-600 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This airworthiness directive (AD) supersedes two existing ADs.
One AD applies to certain Airbus Model A310-200 and -300 series
airplanes. That AD currently requires repetitive inspections for
cracking of the flap transmission shafts, and replacement of the
transmission shafts if necessary. That AD also provides an optional
terminating action for the repetitive inspections. The other existing
AD applies to all Airbus Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model C4-605R Variant F airplanes (collectively called
A300-600 series airplanes); and Model A310-200 and -300 series
airplanes. That AD currently requires a one-time inspection of the
trimmable horizontal stabilizer actuator (THSA), corrective actions if
necessary, and follow-on repetitive tasks. This new AD also requires
revising the Airworthiness Limitations Section of the Instructions for
Continued Airworthiness to incorporate new limitations and maintenance
tasks for aging systems maintenance. This AD results from the
manufacturer's determination that life limitations and maintenance
tasks are necessary to ensure continued operational safety of the
affected airplanes. We are issuing this AD to prevent reduced
structural integrity of these airplanes due to the failure of system
components.
DATES: This AD becomes effective April 28, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of April 28,
2009.
On August 29, 2006 (71 FR 42021, July 25, 2006), the Director of
the Federal Register approved the incorporation by reference of Airbus
Service Bulletin A300-27-6044, Revision 04, dated September 10, 2001;
and Airbus Service Bulletin A310-27-2089, Revision 02, dated June 28,
2001.
On June 20, 2006 (71 FR 28254, May 16, 2006), the Director of the
Federal Register approved the incorporation by reference of Airbus
Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005; and
Airbus Service Bulletin A310-27-2095, dated March 29, 2000.
ADDRESSES: For Airbus service information identified in this AD,
contact Airbus SAS-EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet
https://www.airbus.com. For TRW Aeronautical Systems service information
identified in this AD, contact TRW Syst[egrave]mes A[eacute]ronautiques
Civils SAS, Product Support Department, 7-9 Avenue de l'Eguillette,
Saint Ouen l'Aumone BP 7186, 95056 Cergy-Pontoise Cedex France,
telephone +33 1 34 32 63 00; fax +33 1 34 32 63 10.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and
[[Page 12229]]
other information. The address for the Docket Office (telephone 800-
647-5527) is the Document Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an AD that supersedes two existing
ADs: AD 2006-10-11, amendment 39-14595 (71 FR 28254, May 16, 2006); and
AD 2006-15-10, amendment 39-14690 (71 FR 42021, July 25, 2006). AD
2006-10-11 applies to certain Airbus Model A310-200 and -300 series
airplanes and requires repetitive inspections for cracking of the flap
transmission shafts, and replacing the transmission shafts if
necessary. That existing AD also provides an optional terminating
action for the repetitive inspections. AD 2006-15-10 applies to all
Airbus Model A310 and A300-600 series airplanes and requires a one-time
inspection of the trimmable horizontal stabilizer actuator (THSA),
corrective actions if necessary, and follow-on repetitive tasks.
That supplemental NPRM was published in the Federal Register on
September 26, 2008 (73 FR 55781). That supplemental NPRM proposed to
continue to require the actions required by the two existing ADs. That
supplemental NPRM also proposed to require revising the Airworthiness
Limitations Section of the Instructions for Continued Airworthiness to
incorporate new limitations and maintenance tasks for aging systems
maintenance. In addition, that supplemental NPRM proposed to revise the
original NPRM by reducing the initial compliance times.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been received on the
supplemental NPRM or on the determination of the cost to the public.
Explanation of Changes
We have removed the ``Service Bulletin References'' paragraph in
the ``RESTATEMENT OF REQUIREMENTS OF AD 2006-15-10'' section of this
AD. Instead, we refer to the required service documents in the
individual paragraphs of this AD.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD with the
changes described previously. We also determined that these changes
will not increase the economic burden on any operator or increase the
scope of the AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Action Work hours labor rate Cost per airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2006- 1 $80 $80 per inspection 59 $4,720 per
10-11). cycle. inspection cycle.
Inspection (required by AD 2006- 3 80 $240............... 213 $51,120.
15-10).
Repetitive follow-on tasks 12 80 $960 per inspection 213 $204,480 per
(required by AD 2006-15-10). cycle. inspection cycle.
ALS revision (new action)....... 1 80 $80................ 213 $17,040.
----------------------------------------------------------------------------------------------------------------
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 have 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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) 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. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
[[Page 12230]]
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14595 (71 FR 28254, May 16, 2006), and amendment
39-14690 (71 FR 42021, July 25, 2006), and by adding the following new
airworthiness directive (AD):
2009-06-06 Airbus: Amendment 39-15842. Docket No. FAA-2008-0018;
Directorate Identifier 2007-NM-145-AD.
Effective Date
(a) This AD becomes effective April 28, 2009.
Affected ADs
(b) This AD supersedes AD 2006-10-11 and AD 2006-15-10.
Applicability
(c) This AD applies to all Airbus Model A310 series airplanes;
and Model A300-600 series airplanes; certificated in any category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (q) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued operational safety of the airplane.
Unsafe Condition
(d) This AD results from the manufacturer's determination that
life limitations and maintenance tasks are necessary to ensure
continued operational safety of the affected airplanes. We are
issuing this AD to prevent reduced structural integrity of these
airplanes due to the failure of system components.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006-10-11
Inspection and Corrective Action
(f) For Airbus Model A310-203, -204, -221, -222, -304, -322, -
324, and -325 airplanes, except for airplanes on which Airbus
Modification 12247 has been embodied in production: At the earlier
of the compliance times specified in paragraph (f)(1) or (f)(2) of
this AD, perform a detailed inspection for stress corrosion cracking
of the flight transmission shafts located between the power control
unit (PCU) and the torque limiters in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-27-2092,
Revision 02, dated April 11, 2005. Thereafter, repeat the
inspections as required by paragraph (g) of this AD. Before further
flight, replace any cracked transmission shaft discovered during any
inspection required by this AD with a new or reconditioned shaft, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-27-2095, dated March 29, 2000. Doing an inspection in
accordance with paragraph (n) or (o) of this AD terminates the
requirements of this paragraph.
(1) Within 2,000 flight hours after the last flap asymmetry
protection test performed in accordance with Airbus A310 Maintenance
Planning Document (MPD) Task 275600-01-1.
(2) Within 8,000 flight cycles after the last flap asymmetry
protection test performed in accordance with Airbus A310 MPD Task
275600-02-1 or 800 flight cycles after June 20, 2006 (the effective
date of AD 2006-10-11), whichever comes later.
Note 2: Airbus Service Bulletin A310-27-2092, Revision 02, dated
April 11, 2005, refers to Lucas Liebherr Service Bulletin 551A-27-
624, Revision 1, dated August 18, 2000, as a source of service
information for accomplishing the inspections.
Note 3: Airbus Service Bulletin A310-27-2092, Revision 02, dated
April 11, 2005, refers to Airbus Service Bulletin A310-27-2095,
dated March 29, 2000, as a source of information for replacing the
flap transmission shafts.
Note 4: Airbus Service Bulletin A310-27-2095, dated March 29,
2000, refers to Lucas Liebherr Service Bulletin 551A-27-M551-05,
dated January 12, 2000, as an additional source of information for
replacing the flap transmission shafts.
Repetitive Inspections
(g) Repeat the inspection required by paragraph (f) of this AD
at the applicable times specified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD. Doing an inspection in accordance with paragraph
(n) or (o) of this AD terminates the requirements of this paragraph.
(1) Before further flight after any occurrence of jamming of the
flap transmission system.
(2) At intervals not to exceed 2,000 flight hours after each
flap asymmetry protection test performed in accordance with Airbus
A310 MPD Task 275600-01-1.
(3) At intervals not to exceed 8,000 flight cycles after each
flap asymmetry protection test performed in accordance with Airbus
A310 MPD Task 275600-02-1.
Optional Terminating Action
(h) Replacing any flap transmission shaft with a new or
reconditioned transmission shaft in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-27-2095,
dated March 29, 2000, ends the inspections required by paragraphs
(f) and (g) of this AD for that transmission shaft only.
Actions Performed Using Previously Issued Service Information
(i) Actions performed in accordance with Airbus Service Bulletin
A310-27-2092, dated April 9, 1999; or Revision 01, dated December
11, 2001; are considered acceptable for compliance with the
corresponding requirements of paragraphs (f) and (g) of this AD.
No Reporting
(j) Although Airbus Service Bulletin A310-27-2092, Revision 02,
dated April 11, 2005, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
Restatement of Requirements of AD 2006-15-10
Inspection
(k) At the applicable time specified in paragraph (k)(1) or
(k)(2) of this AD, do a detailed inspection of specified components
of the trimmable horizontal stabilizer actuator (THSA) in accordance
with paragraph 1.E.(2)(a) and the Accomplishment Instructions of the
applicable service bulletin as identified in Table 1 of this AD.
Repair any discrepancy before further flight in accordance with TRW
Aeronautical Systems Horizontal Stabilizer Actuator 47142 Series
Component Maintenance Manual with Illustrated Parts List 27-44-13,
Revision 6, dated September 14, 2001; or a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA, or the European Aviation Safety Agency (EASA) (or
its delegated agent). Doing an inspection in accordance with
paragraph (n) or (o) of this AD terminates the requirements of this
paragraph.
(1) If the flight hours accumulated on the THSA can be
positively determined: Inspect at the earlier of:
(i) Before the accumulation of 47,000 total flight hours on the
THSA, or within 600 flight hours after August 29, 2006 (the
effective date of AD 2006-15-10), whichever occurs later.
(ii) Within 25 years since the THSA was new or within 600 flight
hours after August 29, 2006, whichever occurs later.
(2) If the flight hours accumulated on the THSA cannot be
positively determined: Inspect before the accumulation of 47,000
total flight hours on the airplane, or within 600 flight hours after
August 29, 2006, whichever occurs later.
[[Page 12231]]
Table 1--Service Bulletins for the Requirements of Paragraph (k) of This
AD
------------------------------------------------------------------------
Approved Airbus
Service Bulletin
version for
Required Airbus Service Bulletin actions done Airbus airplane
before the model
effective date of
this AD
------------------------------------------------------------------------
Airbus Service Bulletin A300-27- A300-27-6044, A300 B4-601, B4-
6044, Revision 04, dated Revision 02, 603, B4-620, and
September 10, 2001; or Airbus dated August 26, B4-622.
Mandatory Service Bulletin A300- 2000; or Revision A300 B4-605R and
27-6044, Revision 05, dated 03, dated June B4-622R.
August 29, 2006. 28, 2001. A300 B4-605R and
B4-622R.
A300 C4-605R
Variant F.
Airbus Service Bulletin A310-27- .................. A310-203, -204, -
2089, Revision 02, dated June 221, and -222.
28, 2001; or Airbus Mandatory A310-304, -322, -
Service Bulletin A310-27-2089, 324, and -325.
Revision 03, dated August 29,
2006.
------------------------------------------------------------------------
Note 5: The service bulletins specified in Table 1 of this AD
refer to Goodrich Actuation Systems Service Bulletin 47142-27-11,
Revision 3, dated April 25, 2005, as an additional source of service
information for the required actions.
Note 6: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Follow-on Repetitive Tasks
(l) After the inspection required by paragraph (k) of this AD:
Do the repetitive tasks in accordance with the Accomplishment
Instructions and at the times specified in paragraph 1.E.(2)(b) of
the applicable service bulletin identified in Table 2 of this AD,
except as provided by paragraph (m) of this AD. The repetitive tasks
are valid only until the THSA operational life exceeds 65,000 flight
hours, 40,000 flight cycles, or 25 years, whichever occurs first.
Before the THSA is operated beyond these extended life goals, it
must be replaced with a new or serviceable THSA, except as required
by paragraph (m) of this AD. Doing an inspection in accordance with
paragraph (n) or (o) of this AD terminates the requirements of this
paragraph.
Table 2--Service Bulletins for the Requirements of Paragraph (l) of This
AD
------------------------------------------------------------------------
Approved Airbus
Service Bulletin
version for
Required Airbus Service Bulletin actions done Airbus airplane
before the model
effective date of
this AD
------------------------------------------------------------------------
Airbus Service Bulletin A300-27- A300-27-6044, A300 B4-601, B4-
6044, Revision 04, dated Revision 02, 603, B4-620, and
September 10, 2001; or Airbus dated August 26, B4-622.
Mandatory Service Bulletin A300- 2000; or Revision A300 B4-605R and
27-6044, Revision 05, dated 03, dated June B4-622R.
August 29, 2006. 28, 2001. A300 B4-605R and
B4-622R.
A300 C4-605R
Variant F.
Airbus Service Bulletin A310-27- A310-27-2089, A310-203, -204, -
2089, Revision 02, dated June Revision 01, 221, and -222.
28, 2001; or Airbus Mandatory dated August 25, A310-304, -322, -
Service Bulletin A310-27-2089, 2000. 324, and -325.
Revision 03, dated August 29,
2006.
------------------------------------------------------------------------
Note 7: For additional information on the THSA life limits,
refer to Airbus Operators Information Telex (OIT) SE 999.0074/05/BB,
dated August 3, 2005.
THSA Replacement
(m) For any THSA, whether discrepant or not, that is replaced
with a new or serviceable THSA: Within 47,000 flight hours or 25
years, whichever occurs first, after the THSA is replaced, do the
applicable tasks specified in paragraph 1.E.(2)(a) and the
Accomplishment Instructions of the applicable service bulletin
identified in Table 3. Thereafter repeat the tasks within the
repetitive intervals specified in paragraph 1.E.(2)(b) of the
applicable service bulletin. Doing the corresponding tasks in
accordance with paragraph (n) or (o) of this AD terminates the
requirements of this paragraph.
Table 3--Service Bulletins for the Requirements of Paragraph (m) of This
AD
------------------------------------------------------------------------
Approved Airbus
Service Bulletin
version for
Required Airbus Service Bulletin actions done Airbus airplane
before the model
effective date of
this AD
------------------------------------------------------------------------
Airbus Service Bulletin A300-27- A300-27-6044, A300 B4-601, B4-
6044, Revision 04, dated Revision 02, 603, B4-620, and
September 10, 2001; or Airbus dated August 26, B4-622.
Mandatory Service Bulletin A300- 2000; or Revision A300 B4-605R and
27-6044, Revision 05, dated 03, dated June B4-622R.
August 29, 2006. 28, 2001. A300 F4-605R and
F4-622R.
A300 C4-605R
Variant F.
Airbus Service Bulletin A310-27- A310-27-2089, A310-203, -204, -
2089, Revision 02, dated June Revision 01, 221, and -222.
28, 2001; or Airbus Mandatory dated August 25, A310-304, -322, -
Service Bulletin A310-27-2089, 2000. 324, and -325.
Revision 03, dated August 29,
2006.
------------------------------------------------------------------------
[[Page 12232]]
New Requirements of This AD
Revise Airworthiness Limitations Section (ALS) To Incorporate
Limitations and Maintenance Tasks for Aging Systems Maintenance
(n) Within 3 months after the effective date of this AD, revise
the ALS of the Instructions for Continued Airworthiness (ICA) to
incorporate Airbus A310 ALS Part 4--Ageing Systems Maintenance,
Revision 01, dated December 21, 2006 (for Model A310 series
airplanes); or Airbus A300-600 ALS Part 4--Ageing Systems
Maintenance, Revision 01, dated December 21, 2006 (for Model A300-
600 series airplanes). For all tasks identified in Airbus A310 ALS
Part 4--Ageing Systems Maintenance, Revision 01, dated December 21,
2006; and Airbus A300-600 ALS Part 4--Ageing Systems Maintenance,
Revision 01, dated December 21, 2006; do the tasks at the later of
the times specified in paragraphs (n)(1) and (n)(2) of this AD, as
applicable, except as provided by paragraph (o) of this AD. The
repetitive inspections must be accomplished thereafter at the
interval specified in Airbus A310 ALS Part 4--Ageing Systems
Maintenance, Revision 01, dated December 21, 2006; or Airbus A300-
600 ALS Part 4--Ageing Systems Maintenance, Revision 01, dated
December 21, 2006; as applicable. Doing an inspection required by
this paragraph terminates the corresponding inspection required by
paragraph (f), (g), (k), (l), or (m) of this AD.
(1) At the initial compliance times (thresholds) specified in
Airbus A310 ALS Part 4--Ageing Systems Maintenance, Revision 01,
dated December 21, 2006; or Airbus A300-600 ALS Part 4--Ageing
Systems Maintenance, Revision 01, dated December 21, 2006; as
applicable; with the compliance times starting from the later of the
times specified in paragraphs (n)(1)(i) and (n)(1)(ii) of this AD.
(i) Since first flight of the airplane.
(ii) Since the applicable part was new or refurbished if the
part's life (in flight hours, flight cycles, landings, or calendar
time, as applicable) can be conclusively determined.
(2) Within 3 months after doing the revision of the ALS of the
ICA required by paragraph (o) of this AD.
Note 8: For additional information on the THSA life limits,
refer to Airbus OIT SE 999.0074/05/BB, dated August 3, 2005.
Note 9: For additional information on the THSA life limits and
calculation method for unknown history of parts, refer to Airbus OIT
SE 999.0008/07/LB, dated January 16, 2007; and Airbus Service
Information Letter 05-008, Revision 01, dated February 21, 2007.
(o) For airplanes on which any life limitation/maintenance task
has been complied with in accordance with the requirements of
paragraph (f), (g), (k), (l), or (m) of this AD (e.g., AD 2006-10-11
or AD 2006-15-10), the last accomplishment of each limitation/task
must be retained as a starting point for the accomplishment of each
corresponding limitation/task interval now introduced in Airbus A310
ALS Part 4--Ageing Systems Maintenance, Revision 01, dated December
21, 2006; and Airbus A300-600 ALS Part 4--Ageing Systems
Maintenance, Revision 01, dated December 21, 2006; as applicable.
Doing an inspection required by this paragraph terminates the
corresponding inspection required by paragraph (f), (g), (k), (l),
or (m) of this AD.
(p) Except as provided by paragraph (q) of this AD: After
accomplishing the actions specified in paragraphs (n) and (o) of
this AD, no alternative inspection, inspection intervals, or
limitations may be used.
Alternative Methods of Compliance (AMOCs)
(q)(1) 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.
Send information to ATTN: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-1622; fax (425) 227-1149. Before using any approved AMOC
on any airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) AMOCs approved previously in accordance with AD 2006-10-11
are not approved as AMOCs with this AD.
(3) AMOCs approved previously in accordance with AD 2006-15-10
are not approved as AMOCs with this AD.
Related Information
(r) EASA airworthiness directive 2007-0092, dated April 10,
2007, also addresses the subject of this AD.
Material Incorporated by Reference
(s) You must use the service information identified in Table 4
of this AD, as applicable, to do the actions required by this AD,
unless the AD specifies otherwise. If you accomplish the optional
actions specified by this AD, you must use Airbus Service Bulletin
A310-27-2095, dated March 29, 2000, to perform those actions, unless
the AD specifies otherwise.
Table 4--Material Incorporated by Reference for the Actions Required by This AD
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus A300-600 Airworthiness 01........................ December 21, 2006.
Limitations Section (ALS) Part 4--
Ageing Systems Maintenance.
Airbus A310 Airworthiness Limitations 01........................ December 21, 2006.
Section (ALS) Part 4--Ageing Systems
Maintenance.
Airbus Mandatory Service Bulletin A300- 05........................ August 29, 2006.
27-6044.
Airbus Mandatory Service Bulletin A310- 03........................ August 29, 2006.
27-2089.
Airbus Service Bulletin A300-27-6044... 04........................ September 10, 2001.
Airbus Service Bulletin A310-27-2089... 02........................ June 28, 2001.
Airbus Service Bulletin A310-27-2092... 02........................ April 11, 2005.
Airbus Service Bulletin A310-27-2095... Original.................. March 29, 2000.
TRW Aeronautical Systems Horizontal 6......................... September 14, 2001.
Stabilizer Actuator 47142 Series
Component Maintenance Manual with
Illustrated Parts List 27-44-13.
----------------------------------------------------------------------------------------------------------------
(TRW Aeronautical Systems Horizontal Stabilizer Actuator 47142
Series Component Maintenance Manual with Illustrated Parts List 27-
44-13 contains the following discrepancies: The revision level of
the document is only specified on the Letter of Transmittal; the
Letter of Transmittal is not specified in the List of Effective
Pages; and the List of Effective Pages refers to page 748a as 748b.)
(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 5 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
Table 5--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus A300-600 Airworthiness 01........................ December 21, 2006.
Limitations Section (ALS) Part 4--
Ageing Systems Maintenance.
Airbus A310 Airworthiness Limitations 01........................ December 21, 2006.
Section (ALS) Part 4--Ageing Systems
Maintenance.
Airbus Mandatory Service Bulletin A300- 05........................ August 29, 2006.
27-6044.
Airbus Mandatory Service Bulletin A310- 03........................ August 29, 2006.
27-2089.
[[Page 12233]]
TRW Aeronautical Systems Horizontal Original.................. September 14, 2001.
Stabilizer Actuator 47142 Series
Component Maintenance Manual with
Illustrated Parts List 27-44-13.
----------------------------------------------------------------------------------------------------------------
(2) The Director of the Federal Register previously approved the
incorporation by reference of the service information contained in
Table 6 of this AD on August 29, 2006 (71 FR 42021, July 25, 2006).
Table 6--Material Previously Incorporated by Reference in AD 2006-15-10
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A300-27-6044......... 04 September 10, 2001.
Airbus Service Bulletin A310-27-2089......... 02 June 28, 2001.
----------------------------------------------------------------------------------------------------------------
(3) The Director of the Federal Register previously approved the
incorporation by reference of the service information contained in
Table 7 of this AD on June 20, 2006 (71 FR 28254, May 16, 2006).
Table 7--Material Previously Incorporated by Reference in AD 2006-10-11
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A310-27-2092... 02........................ April 11, 2005.
Airbus Service Bulletin A310-27-2095... Original.................. March 29, 2000.
----------------------------------------------------------------------------------------------------------------
(4) For Airbus service information identified in this AD,
contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(5) For TRW Aeronautical Systems service information identified
in this AD, contact TRW Syst[eacute]mes Aeacute;ronautiques Civils
SAS, Product Support Department, 7-9 Avenue de l'Eguillette, Saint
Ouen l'Aumone BP 7186, 95056 Cergy-Pontoise Cedex France, telephone
+33 1 34 32 63 00; fax +33 1 34 32 63 10.
(6) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(7) You may also review copies of the service information
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/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on February 27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-5969 Filed 3-23-09; 8:45 am]
BILLING CODE 4910-13-P
