[Federal Register: January 14, 2008 (Volume 73, Number 9)]
[Proposed Rules]
[Page 2197-2200]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14ja08-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0018; Directorate Identifier 2007-NM-145-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes and
A300-600 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede two existing airworthiness
directives (ADs). One existing AD applies to certain Airbus Model A310
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. The other existing AD 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. This
proposed AD would require revising the Airworthiness Limitations
Section of the Instructions for Continued Airworthiness to incorporate
new limitations and maintenance tasks for aging systems maintenance.
This proposed AD results from the manufacturer's determination that
life limitations and maintenance tasks are necessary in order to ensure
continued operational safety of the affected airplanes. We are
proposing this AD to prevent reduced structural integrity of these
airplanes due to the failure of system components.
DATES: We must receive comments on this proposed AD by February 13,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov.
Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tom 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0018;
Directorate Identifier 2007-NM-145-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On May 8, 2006, we issued AD 2006-10-11, amendment 39-14595 (71 FR
28254, May 16, 2006), for certain Airbus Model A310 series airplanes.
That AD requires repetitive inspections for cracking of the flap
transmission shafts, and replacing the transmission shafts if
necessary. That AD also provides an optional terminating action for the
repetitive inspections. That AD resulted from reports of longitudinal
cracks due to stress corrosion in the transmission
[[Page 2198]]
shafts between the power control unit (PCU) and the torque limiters of
the flap transmission system. We issued that AD to detect and correct
cracking of the flap transmission shaft, which could compromise shaft
structural integrity and lead to a disabled flap transmission shaft and
reduced controllability of the airplane.
On July 14, 2006, we issued AD 2006-15-10, amendment 39-14690 (71
FR 42021, July 25, 2006), for 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 AD resulted from reports of THSAs
that have reached their design operational life. We issued that AD to
extend the operational life of the THSA to prevent a possible failure
of high-time THSAs, which could result in reduced controllability of
the airplane.
Actions Since Existing ADs Were Issued
Since we issued ADs 2006-10-11 and 2006-15-10, the European
Aviation Safety Agency (EASA), which is the Technical Agent for the
Member States of the European Community, notified us that an unsafe
condition may exist on all Airbus Model A310 and A300-600 series
airplanes. The EASA advises that Airbus has issued aging system
maintenance limitations and maintenance tasks to address airplane
systems that operate beyond their original limits, which could result
in increased potential for failure of these systems and consequent
reduced structural integrity of these airplanes.
Relevant Service Information
Airbus has issued A300-600 ALS--Airworthiness Limitations Section,
and A310 ALS--Airworthiness Limitations Section, both dated May 31,
2006, which are a repository for stand-alone documents that are
approved independently from each other. The Airbus ALSs comprises the
following documents:
ALS Part 1--Safe Life Airworthiness Limitation Items
ALS Part 2--Damage-Tolerant Airworthiness Limitation Items
ALS Part 3--Certification Maintenance Requirements
ALS Part 4--Aging Systems Maintenance
ALS Part 5--Fuel Airworthiness Limitations
Airbus A310 ALS Part 4--Aging Systems Maintenance, Revision 01,
dated December 21, 2006, and A300-600 ALS Part 4--Aging Systems
Maintenance, Revision 01, dated December 21, 2006, describe aging
system maintenance limitations and maintenance tasks.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The EASA mandated
the service information and issued airworthiness directive 2007-0092,
dated April 10, 2007, to ensure the continued airworthiness of these
airplanes in the European Union.
FAA's Determination and Requirements of the Proposed AD
These airplanes are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, EASA has kept the FAA informed of
the situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede ADs 2006-10-11 and 2006-15-10 and
would retain the requirements of the existing ADs. This proposed AD
would also require revising the Airworthiness Limitations Section (ALS)
of the Instructions for Continued Airworthiness to incorporate new
limitations and maintenance tasks for aging systems maintenance. Doing
an inspection in accordance with the ALS revision would terminate the
requirements of the existing ADs.
Explanation of Change to Applicability
We have revised the applicability of the existing ADs to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
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Number of U.S.-
Action Work hours Average labor Cost per airplane registered Fleet cost
rate per hour airplanes
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Inspection (required by AD 2006-10- 1 $80 $80, per inspection cycle........ 59 $4,720, per inspection cycle.
11).
Inspection (required by AD 2006-15- 3 80 240.............................. 213 51,120.
10).
Repetitive follow-on tasks 12 80 960, per inspection cycle........ 213 204,480, per inspection cycle.
(required by AD 2006-15-10).
ALS Revision (new proposed action) 1 80 80............................... 213 17,040.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and
[[Page 2199]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); 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 proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
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 adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA-2008-0018; Directorate Identifier 2007-NM-
145-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by February
13, 2008.
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 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 (r) 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. The FAA has
provided guidance for this determination in Advisory Circular (AC)
25-1529-1.
Unsafe Condition
(d) This AD results from the manufacturer's determination that
life limitations and maintenance tasks are necessary in order 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 (o) or (p) 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 an additional source of
service information for accomplishing the inspections.
Note 3: Airbus Service Bulletin A310-27-2092, Revision 02,
refers to Airbus Service Bulletin A310-27-2095, dated March 29,
2000, as a source of service information for replacing the flap
transmission shafts.
Note 4: Airbus Service Bulletin A310-27-2095 refers to Lucas
Liebherr Service Bulletin 551A-27-M551-05, dated January 12, 2000,
as an additional source of service 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
(o) or (p) 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
Service Bulletin References
(k) Unless otherwise specified in this AD, the term ``service
bulletin,'' as used in paragraphs (l), (m), and (n) of this AD,
means the applicable required service bulletin identified in Table 1
of this AD. The service bulletins 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.
[[Page 2200]]
Table 1.--Service Bulletins
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Approved Airbus
Service Bulletin
Required Airbus Service version for actions Airbus airplane
Bulletin done before the model
effective date of
this AD
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A300-27-6044, Revision 04, A300-27-6044, A300 B4-601, B4-603,
dated September 10, 2001. Revision 02, dated B4-620, and B4-622.
August 26, 2000; or A300 B4-605R and B4-
Revision 03, dated 622R.
June 28, 2001. A300 F4-605R and F4-
622R.
A300 C4-605R Variant
F.
A310-27-2089, Revision 02, A310-27-2089, A310-203, -204, -
dated June 28, 2001. Revision 01, dated 221, and -222.
August 25, 2000. A310-304, -322, -
324, and -325.
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Inspection
(l) At the applicable time specified in paragraph (l)(1) or
(l)(2) of this AD, do a detailed inspection of specified components
of the THSA in accordance with paragraph 1.E.(2)(a) and the
Accomplishment Instructions of the applicable service bulletin.
Repair any discrepancy before further flight in accordance with 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). TRW Aeronautical Systems/
Lucas Aerospace Component Maintenance Manual 27-44-13, dated
September 14, 2001, is one acceptable method for the repair. Doing
an inspection in accordance with paragraph (o) or (p) 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.
Note 5: 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
(m) After the inspection required by paragraph (l) 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 service bulletin, as applicable, except as provided by paragraph
(n) 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
THSA, except as required by paragraph (n) of this AD. Doing an
inspection in accordance with paragraph (o) or (p) of this AD
terminates the requirements of this paragraph.
THSA Replacement
(n) For any THSA, whether discrepant or not, that is replaced
with a new 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. 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 (o) or (p) of this
AD terminates the requirements of this paragraph.
New Requirements of This AD
Revise Airworthiness Limitations Section (ALS) to Incorporate
Limitations and Maintenance Tasks for Aging Systems Maintenance
(o) Within 3 months after the effective date of this AD, revise
the Airworthiness Limitations Section (ALS) of the Instructions for
Continued Airworthiness to incorporate Airbus A310 ALS Part 4--Aging
Systems Maintenance, Revision 01, dated December 21, 2006; and A300-
600 ALS Part 4--Aging Systems Maintenance, Revision 01, dated
December 21, 2006; as applicable. For all tasks identified in Airbus
A310 ALS Part 4--Aging Systems Maintenance, Revision 01; and A300-
600 ALS Part 4--Aging Systems Maintenance, Revision 01; the initial
compliance times start from the effective date of this AD, except as
provided by paragraph (p) of this AD. The repetitive inspections
must be accomplished thereafter at the interval specified in Airbus
A310 ALS Part 4--Aging Systems Maintenance, Revision 01; and A300-
600 ALS Part 4--Aging Systems Maintenance, Revision 01.
(p) For airplanes on which any life limitation/maintenance task
has been complied with in accordance with the requirements of 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--Aging Systems Maintenance,
Revision 01, dated December 21, 2006; and A300-600 ALS Part 4--Aging
Systems Maintenance, Revision 01, dated December 21, 2006; as
applicable.
(q) Except as provided by paragraph (r) of this AD: After
accomplishing the actions specified in paragraphs (o) and (p) of
this AD, no alternative inspection, inspection intervals, or
limitations may be used.
Alternative Methods of Compliance (AMOCs)
(r)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
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.
(3) AMOCs approved previously in accordance with AD 2006-10-11
are not approved as AMOCs with this AD.
(4) AMOCs approved previously in accordance with AD 2006-15-10
are not approved as AMOCs with this AD.
Related Information
(s) EASA airworthiness directive 2007-0092, dated April 10,
2007, also addresses the subject of this AD.
Issued in Renton, Washington, on January 3, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-380 Filed 1-11-08; 8:45 am]
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