

[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
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                       Number of U.S.-
              Action                  Work hours     Average labor          Cost per airplane            registered                Fleet cost
                                                     rate per hour                                        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
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.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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
------------------------------------------------------------------------
                                 Approved Airbus
                                Service Bulletin
   Required Airbus Service     version for actions     Airbus airplane
          Bulletin               done before the            model
                                effective date of
                                     this AD
------------------------------------------------------------------------
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.
------------------------------------------------------------------------

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]

BILLING CODE 4910-13-P
