[Federal Register Volume 73, Number 188 (Friday, September 26, 2008)]
[Proposed Rules]
[Pages 55781-55786]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-22632]


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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 
Model A300-600 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: The FAA is revising an earlier NPRM for an airworthiness 
directive (AD) that applies to all Airbus Model A310 series airplanes 
and Model A300-600 series airplanes. The original NPRM would have 
required superseding two existing ADs. One existing AD applies to 
certain Airbus Model A310 series airplanes and currently requires

[[Page 55782]]

repetitive inspections for cracking of the flap transmission shafts, 
and replacement of 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 currently requires a one-time inspection 
of the trimmable horizontal stabilizer actuator, corrective actions if 
necessary, and follow-on repetitive tasks. The original NPRM would have 
added revising the Airworthiness Limitations Section of the 
Instructions for Continued Airworthiness to incorporate new limitations 
and maintenance tasks for aging systems maintenance. The original NPRM 
resulted from the manufacturer's determination that life limitations 
and maintenance tasks are necessary in order to ensure continued 
operational safety of the affected airplanes. This new action revises 
the original NPRM by reducing the initial compliance times. We are 
proposing this supplemental NPRM to prevent reduced structural 
integrity of these airplanes due to the failure of system components.

DATES: We must receive comments on this supplemental NPRM by October 
21, 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

    The FAA issued a notice of proposed rulemaking (NPRM) (the 
``original 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), which applies to certain Airbus Model A310 series 
airplanes; and AD 2006-15-10, amendment 39-14690 (71 FR 42021, July 25, 
2006), which applies to all Airbus Model A310 and A300-600 series 
airplanes. The original NPRM was published in the Federal Register on 
January 14, 2008 (73 FR 2197). The original NPRM applies to all Airbus 
Model A310 series airplanes and Model A300-600 series airplanes. The 
original NPRM proposed to retain the requirements of the existing ADs. 
The original NPRM also proposed to add revising the Airworthiness 
Limitations Section (ALS) of the Instructions for Continued 
Airworthiness (ICA) to incorporate new limitations and maintenance 
tasks for aging systems maintenance.

Actions Since Original NPRM Was Issued

    Since the original NPRM was issued, we have determined that the 
initial compliance times for the revision specified in paragraph (o) of 
the original NPRM need to be reduced. In paragraph (o) of the original 
NPRM, we specified that for all tasks ``* * * the initial compliance 
times start from the effective date of this AD * * *.'' However, the 
thresholds specified in Airbus A310 ALS Part 4--Aging Systems 
Maintenance, Revision 01, dated December 21, 2006; and Airbus A300-600 
ALS Part 4--Aging Systems Maintenance, Revision 01, dated December 21, 
2006; (which are referred to as the appropriate sources of service 
information for accomplishing the required actions in paragraph (o) of 
the original NPRM); start from ``* * * the initial entry into service 
of a specific maintenance task.''
    In order to ensure timely action to address the identified unsafe 
condition, we have reduced the initial compliance times in order to 
match the service information. We have revised paragraph (o) of the 
supplemental NPRM accordingly.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the original NPRM.

Request To Refer to Latest Revisions of Service Bulletins

    Federal Express (FedEx) requests that we refer to the latest 
revision 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 (which are referred to in Table 1 of paragraph 
(k) of the original NPRM as the appropriate sources of service 
information for doing the actions specified in paragraphs (l), (m), and 
(n) of the original NPRM). FedEx states that Airbus Service Bulletin 
A300-27-6044, Revision 05, dated August 29, 2006; and Airbus Service 
Bulletin A310-27-2089, Revision 03, dated August 29, 2006; do not 
specify any additional work and were primarily issued to adjust the 
service bulletin effectivity as well as to provide additional reference 
data.
    We agree with the commenter to refer to Airbus Service Bulletin 
A300-27-6044, Revision 05, dated August 29, 2006; and Airbus Service 
Bulletin A310-27-2089, Revision 03, dated August 29, 2006. We have 
reviewed the service bulletins and determined no additional work is 
required. We have revised Table 1 of this supplemental NPRM 
accordingly.

[[Page 55783]]

Request To Clarify Definition of ``New''

    FedEx requests that we clarify the word ``new'' specified in 
paragraph (m) of the original NPRM. FedEx states that the word ``new'' 
pertains to the replacement of the trimmable horizontal stabilizer 
actuator (THSA), and the replacement could be with a new or used 
(serviceable) THSA provided that the THSA has not been operated more 
than 65,000 flight hours or 40,000 flight cycles or been in service 
more than 25 years since new, whichever occurs first. FedEx also states 
that if an THSA that was operated more than 47,000 flight hours has 
been installed, it must be inspected in accordance with Airbus Service 
Bulletins A300-27-6044 or A310-27-2089 (as specified in paragraph (n) 
of the original NPRM). FedEx further states that Airbus is in 
concurrence with FedEx's comment.
    We agree with the commenter that the replacement specified in 
paragraph (m) of this supplemental NPRM could be with a new or 
serviceable THSA. Sub-part 4-2 of the Airbus A300-600 and A310 ALS Part 
4 lists the life limits for the operational life of the listed 
components. When a component (e.g., the THSA) reaches the earliest of 
any of the life limits in flight hours, flight cycles, or calendar 
time, that component has reached the end of its given operational life 
and must be removed from the airplane and replaced by another unit. It 
is not necessary that the replacement unit/component be ``new.'' The 
rules of application for the ALS Part 4 are given in sub-part 4-0 of 
the ALS.
    It is a requirement that a life-limited component not be operated 
beyond the limitation stated in the ALS Part 4-2. Thus, for the THSA, 
as long as none of the limits (65,000 flight hours, 40,000 flight 
cycles, or 25 years of operation) have been exceeded and the component 
is classified ``serviceable,'' then the component can be installed and 
operated on the airplane. Airbus Operators Information Telex (OIT) SE 
999.0074/05/BB, dated August 3, 2005, provides clarification on these 
limits. We have revised paragraph (m) of this supplemental NPRM to 
clarify that the installed part may be ``new'' or ``serviceable,'' and 
we have added Note 6 and Note 7 to this supplemental NPRM to refer to 
the OIT for clarification of these limits.

Request To Clarify Starting Point of 25-Year Life Limit

    FedEx requests that we clarify the starting point for the 25-year 
life limit specified in the Airbus A300-600 and A310 ALS Part 4 for 
THSAs built as spare parts and not originally installed on airplanes. 
FedEx suggests that operators be required to use the date of 
manufacture of the THSA as documented by Goodrich, the original 
equipment manufacturer (OEM) of the THSA. FedEx states that it would be 
difficult to determine when the component, produced as a spare by 
Goodrich, was first installed on an airplane.
    We agree to clarify the starting point for the 25-year life limit. 
The ALS Part 4 does not provide the calendar limit guidance that is 
provided in Airbus Service Information Letter (SIL) 05-008, dated July 
7, 2006. Airbus issued SIL 05-008 to give guidance (i.e., a calculation 
method) for life limitations in calendar parameters for components 
whose history is partially or completely unknown. This calculation 
method could be used by operators when they comply with the ALS Parts 
4-2 and 4-3(a).
    The SIL is intended for use when operators cannot retrieve their 
parts history (in flight hours/flight cycles). This method provides an 
estimated parts life (flight hours/flight cycles) and is very 
conservative. As suggested in the FedEx request, one method employed in 
the life calculation (starting point) is the date of manufacture (DOM). 
The DOM is shown in one of the tables and examples within the SIL.
    The SIL is not currently referenced in the ALS Part 4. However, 
Airbus has issued OIT SE 999.0008/07/LB, dated January 16, 2007. 
Section 4 of the OIT advises users of the availability of SIL 05-008. 
We have added Note 8 to this supplemental NPRM to refer to the OIT and 
SIL for clarification.

Request To Include New THSA Part

    FedEx requests that we include the new configuration of THSA, part 
number (P/N) 47142-323, and its life limitation. FedEx states that P/N 
47142-323 does not have the 25-year life limit due to the application 
of enhanced materials and processes used during manufacture to 
reinforce their resistance to corrosion. FedEx notes that Airbus issued 
Service Bulletins A300-27-6058 and A310-27-2100, both dated August 30, 
2007, to introduce this new THSA configuration, which does not carry a 
calendar life limit. FedEx further states that ALS Part 4 does not 
address this THSA configuration.
    We do not agree to include the new THSA part number. We acknowledge 
that Airbus Service Bulletins A300-27-6058 (for Model A300-600 
airplanes) and A310-27-2100 (for Model A310 airplanes) specify 
procedures to install THSA P/N 47142-323. However, Airbus has not 
published a revised inspection task that will apply to P/N 47142-323 to 
address the corrosion issue. After this task has been published, 
operators may request an alternative method of compliance (AMOC) 
according to the provisions of paragraph (r) of this supplemental NPRM. 
We have not revised this supplemental NPRM in this regard.

Request To Allow Additional Compliance Time

    FedEx requests that we add a grace period of 1,200 flight hours for 
Task Number 274411-12-1. FedEx states that the task is contained within 
Airbus A310 ALS Part 4--Aging Systems Maintenance, Revision 01, dated 
December 21, 2006; and Airbus A300-600 ALS Part 4--Aging Systems 
Maintenance, Revision 01, dated December 21, 2006; which were referred 
to in paragraph (o) of the original NPRM for the incorporation of new 
limitations and maintenance tasks for aging systems maintenance. FedEx 
states that the task establishes a threshold for accomplishment at 
47,000 flight hours or 20 years, whichever occurs first, but does not 
provide a grace period for the inspection on actuators that have 
exceeded 20 years in service but not yet reached 25 years in service 
(the established life limit of the THSA). FedEx suggests a grace period 
of 1,200 flight hours to provide sufficient time to sequence airplanes 
through maintenance for accomplishment of this THSA inspection at the 
new established threshold.
    We agree that a grace period is necessary. In accordance with 
paragraph (o) of this supplemental NPRM, operators have three months to 
revise the ALS of the ICA to incorporate the tasks specified 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. For the initial compliance 
times for the tasks identified in the ALS, we have added paragraph 
(o)(2) of this supplemental NPRM to provide a grace period of within 3 
months after revising the ALS of the ICA.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    The changes discussed above expand the scope of the original NPRM; 
therefore, we have determined that it is necessary to reopen the 
comment period to provide additional opportunity for public comment on 
this supplemental NPRM.

[[Page 55784]]

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this supplemental NPRM.

                                                 Estimated Costs
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                                                                                 Number of U.S.-
            Action               Work hours     Average labor      Cost per        registered       Fleet cost
                                                rate per hour      airplane         airplanes
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Inspection (required by AD                  1             $80  $80, per                      59  $4,720, per
 2006-10-11).                                                   inspection                        inspection
                                                                cycle.                            cycle.
Inspection (required by AD                  3              80  $240............             213  $51,120.
 2006-15-10).
Repetitive follow-on tasks                 12              80  $960, per                    213  $204,480, per
 (required by AD 2006-15-10).                                   inspection                        inspection
                                                                cycle.                            cycle.
ALS revision (new 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 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 supplemental NPRM 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 October 
21, 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 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 (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.

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

[[Page 55785]]

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.

                       Table 1--Service Bulletins
------------------------------------------------------------------------
                                    Approved Airbus
                                   Service Bulletin
                                      version for
Required Airbus Service Bulletin     actions done       Airbus airplane
                                      before the             model
                                   effective date of
                                        this AD
------------------------------------------------------------------------
A300-27-6044, Revision 04, dated  A300-27-6044,       A300 B4-601, B4-
 September 10, 2001; or A300-27-   Revision 02,        603, B4-620, and
 6044, Revision 05, dated August   dated August 26,    B4-622.
 29, 2006.                         2000; or Revision  A300 B4-605R and
                                   03, dated June      B4-622R.
                                   28, 2001.          A300 F4-605R and
                                                       F4-622R.
                                                      A300 C4-605R
                                                       Variant F.
A310-27-2089, Revision 02, dated  A310-27-2089,       A310-203, -204, -
 June 28, 2001; or A310-27-2089,   Revision 01,        221, and -222
 Revision 03, dated August 29,     dated August 25,   A310-304, -322, -
 2006.                             2000.               324, and -325.
------------------------------------------------------------------------

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 trimmable horizontal stabilizer actuator (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 or 
serviceable 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.

    Note 6: Refer to Airbus Operators Information Telex (OIT) SE 
999.0074/05/BB, dated August 3, 2005, for additional information on 
the THSA life limits.

THSA Replacement

    (n) 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. 
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

[[Page 55786]]

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 ALS of the Instructions for Continued Airworthiness (ICA) to 
incorporate Airbus A310 ALS Part 4--Aging Systems Maintenance, 
Revision 01, dated December 21, 2006; or Airbus 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 Airbus A300-600 ALS Part 
4--Aging Systems Maintenance, Revision 01; do the tasks at the later 
of the times specified in paragraphs (o)(1) and (o)(2) 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 Airbus A300-600 ALS Part 4--Aging Systems 
Maintenance, Revision 01. Doing an inspection required by this 
paragraph terminates the corresponding inspection required by 
paragraph (f), (g), (l), (m), or (n) of this AD.
    (1) At the initial compliance times (thresholds) specified in 
the applicable ALS Part 4--Aging Systems Maintenance, with the 
compliance times starting from the later of the times specified in 
paragraphs (o)(1)(i) and (o)(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 7: Refer to Airbus OIT SE 999.0074/05/BB, dated August 3, 
2005, for additional information on the THSA life limits.


    Note 8: Refer to Airbus OIT SE 999.0008/07/LB, dated January 16, 
2007; and Airbus Service Information Letter (SIL) 05-008, Revision 
1, dated February 21, 2007; for additional information on the THSA 
life limits and calculation method for unknown history of parts.

    (p) For airplanes on which any life limitation/maintenance task 
has been complied with in accordance with the requirements of 
paragraph (f), (g), (l), (m), or (n) 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--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. Doing an 
inspection required by this paragraph terminates the corresponding 
inspection required by paragraph (f), (g), (l), (m), or (n) of this 
AD.
    (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 using the procedures found in 14 CFR 39.19. 
Send information to ATTN: 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. 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

    (s) EASA airworthiness directive 2007-0092, dated April 10, 
2007, also addresses the subject of this AD.

    Issued in Renton, Washington, on September 18, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-22632 Filed 9-25-08; 8:45 am]
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