
[Federal Register: March 24, 2009 (Volume 74, Number 55)]
[Rules and Regulations]               
[Page 12228-12233]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24mr09-2]                         

-----------------------------------------------------------------------

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 
http://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 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 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.
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    (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 http://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: http://
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
