Airworthiness Directives; Airbus Model A310 Series Airplanes and A300-600 Series Airplanes, 2197-2200 [E8-380]
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Compliance
DEPARTMENT OF TRANSPORTATION
(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.
Federal Aviation Administration
14 CFR Part 39
Inspection and Corrective/Other Specified
Actions if Necessary
[Docket No. FAA–2008–0018; Directorate
Identifier 2007–NM–145–AD]
(f) Within 60 months after the effective
date of this AD, do a general visual
inspection to determine the manufacturer
and manufacture date of the oxygen masks in
the passenger service units and the lavatory
and attendant box assemblies, and do the
applicable corrective action, by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 757–35–0028, dated April 9,
2007; except where the service bulletin
specifies repairing the oxygen mask
assembly, replace it with a new or modified
oxygen mask assembly having an improved
flow indicator. The corrective action and
other specified action must be done before
further flight.
Note 1: The service bulletin refers to B/E
Aerospace Service Bulletin 174080–35–01,
dated February 6, 2006; and Revision 1,
dated May 1, 2006; as additional sources of
service information for modifying the oxygen
mask assembly by replacing the flow
indicator with an improved flow indicator.
RIN 2120–AA64
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, Seattle Aircraft
Certification Office, 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.
Issued in Renton, Washington, on
December 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–376 Filed 1–11–08; 8:45 am]
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Airworthiness Directives; Airbus Model
A310 Series Airplanes and A300–600
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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
https://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
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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 https://
www.regulations.gov; or in person at the
Docket Management Facility between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this 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 https://
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
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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.
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.
FAA’s Determination and Requirements
of the Proposed AD
These airplanes are manufactured in
France and are type certificated for
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
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
ESTIMATED COSTS
Action
Average labor
rate per hour
Work hours
Inspection (required by AD 2006–10–11)
1
$80
Inspection (required by AD 2006–15–10)
Repetitive follow-on tasks (required by
AD 2006–15–10).
ALS Revision (new proposed action) .......
3
12
80
80
1
80
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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,
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Cost per airplane
$80, per inspection
cycle.
240 ..............................
960, per inspection
cycle.
80 ................................
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
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Number of
U.S.-registered
airplanes
Sfmt 4702
59
213
213
213
Fleet cost
$4,720, per inspection
cycle.
51,120.
204,480, per inspection
cycle.
17,040.
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
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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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14595 (71
FR 28254, May 16, 2006) and
amendment 39–14690 (71 FR 42021,
July 25, 2006) and 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.
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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
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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.
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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.
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TABLE 1.—SERVICE BULLETINS
Required Airbus Service Bulletin
Approved Airbus Service Bulletin version for
actions done before the effective
date of this AD
A300–27–6044, Revision 04, dated September
10, 2001.
A300–27–6044, Revision 02, dated August
26, 2000; or Revision 03, dated June 28,
2001.
A310–27–2089, Revision 02, dated June 28,
2001.
A310–27–2089, Revision 01, dated August
25, 2000.
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Inspection
(l) At the applicable time specified in
paragraph (l)(1) or (l)(2) of this AD, do a
detailed inspection of specified components
of the THSA in accordance with paragraph
1.E.(2)(a) and the Accomplishment
Instructions of the applicable service
bulletin. Repair any discrepancy before
further flight in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
Safety Agency (EASA) (or its delegated
agent). TRW Aeronautical Systems/Lucas
Aerospace Component Maintenance Manual
27–44–13, dated September 14, 2001, is one
acceptable method for the repair. Doing an
inspection in accordance with paragraph (o)
or (p) of this AD terminates the requirements
of this paragraph.
(1) If the flight hours accumulated on the
THSA can be positively determined: Inspect
at the earlier of:
(i) Before the accumulation of 47,000 total
flight hours on the THSA, or within 600
flight hours after August 29, 2006 (the
effective date of AD 2006–15–10), whichever
occurs later.
(ii) Within 25 years since the THSA was
new or within 600 flight hours after August
29, 2006, whichever occurs later.
(2) If the flight hours accumulated on the
THSA cannot be positively determined:
Inspect before the accumulation of 47,000
total flight hours on the airplane, or within
600 flight hours after August 29, 2006,
whichever occurs later.
Note 5: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Follow-on Repetitive Tasks
(m) After the inspection required by
paragraph (l) of this AD: Do the repetitive
tasks in accordance with the
Accomplishment Instructions and at the
times specified in paragraph 1.E.(2)(b) of the
service bulletin, as applicable, except as
provided by paragraph (n) of this AD. The
repetitive tasks are valid only until the THSA
operational life exceeds 65,000 flight hours,
40,000 flight cycles, or 25 years, whichever
occurs first. Before the THSA is operated
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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,
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Airbus airplane model
A300 B4–601, B4–603, B4–620, and B4–622.
A300 B4–605R and B4–622R.
A300 F4–605R and F4–622R.
A300 C4–605R Variant F.
A310–203, –204, –221, and –222.
A310–304, –322, –324, and –325.
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0014; Directorate
Identifier 2007–NM–249–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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[Federal Register Volume 73, Number 9 (Monday, January 14, 2008)]
[Proposed Rules]
[Pages 2197-2200]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-380]
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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 https://
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 https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this 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 https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On May 8, 2006, we issued AD 2006-10-11, amendment 39-14595 (71 FR
28254, May 16, 2006), for certain Airbus Model A310 series airplanes.
That AD requires repetitive inspections for cracking of the flap
transmission shafts, and replacing the transmission shafts if
necessary. That AD also provides an optional terminating action for the
repetitive inspections. That AD resulted from reports of longitudinal
cracks due to stress corrosion in the transmission
[[Page 2198]]
shafts between the power control unit (PCU) and the torque limiters of
the flap transmission system. We issued that AD to detect and correct
cracking of the flap transmission shaft, which could compromise shaft
structural integrity and lead to a disabled flap transmission shaft and
reduced controllability of the airplane.
On July 14, 2006, we issued AD 2006-15-10, amendment 39-14690 (71
FR 42021, July 25, 2006), for all Airbus Model A310 and A300-600 series
airplanes and requires a one-time inspection of the trimmable
horizontal stabilizer actuator (THSA), corrective actions if necessary,
and follow-on repetitive tasks. That AD resulted from reports of THSAs
that have reached their design operational life. We issued that AD to
extend the operational life of the THSA to prevent a possible failure
of high-time THSAs, which could result in reduced controllability of
the airplane.
Actions Since Existing ADs Were Issued
Since we issued ADs 2006-10-11 and 2006-15-10, the European
Aviation Safety Agency (EASA), which is the Technical Agent for the
Member States of the European Community, notified us that an unsafe
condition may exist on all Airbus Model A310 and A300-600 series
airplanes. The EASA advises that Airbus has issued aging system
maintenance limitations and maintenance tasks to address airplane
systems that operate beyond their original limits, which could result
in increased potential for failure of these systems and consequent
reduced structural integrity of these airplanes.
Relevant Service Information
Airbus has issued A300-600 ALS--Airworthiness Limitations Section,
and A310 ALS--Airworthiness Limitations Section, both dated May 31,
2006, which are a repository for stand-alone documents that are
approved independently from each other. The Airbus ALSs comprises the
following documents:
ALS Part 1--Safe Life Airworthiness Limitation Items
ALS Part 2--Damage-Tolerant Airworthiness Limitation Items
ALS Part 3--Certification Maintenance Requirements
ALS Part 4--Aging Systems Maintenance
ALS Part 5--Fuel Airworthiness Limitations
Airbus A310 ALS Part 4--Aging Systems Maintenance, Revision 01,
dated December 21, 2006, and A300-600 ALS Part 4--Aging Systems
Maintenance, Revision 01, dated December 21, 2006, describe aging
system maintenance limitations and maintenance tasks.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The EASA mandated
the service information and issued airworthiness directive 2007-0092,
dated April 10, 2007, to ensure the continued airworthiness of these
airplanes in the European Union.
FAA's Determination and Requirements of the Proposed AD
These airplanes are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, EASA has kept the FAA informed of
the situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede ADs 2006-10-11 and 2006-15-10 and
would retain the requirements of the existing ADs. This proposed AD
would also require revising the Airworthiness Limitations Section (ALS)
of the Instructions for Continued Airworthiness to incorporate new
limitations and maintenance tasks for aging systems maintenance. Doing
an inspection in accordance with the ALS revision would terminate the
requirements of the existing ADs.
Explanation of Change to Applicability
We have revised the applicability of the existing ADs to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
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Number of U.S.-
Action Work hours Average labor Cost per airplane registered Fleet cost
rate per hour airplanes
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Inspection (required by AD 2006-10- 1 $80 $80, per inspection cycle........ 59 $4,720, per inspection cycle.
11).
Inspection (required by AD 2006-15- 3 80 240.............................. 213 51,120.
10).
Repetitive follow-on tasks 12 80 960, per inspection cycle........ 213 204,480, per inspection cycle.
(required by AD 2006-15-10).
ALS Revision (new proposed action) 1 80 80............................... 213 17,040.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and
[[Page 2199]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14595 (71 FR 28254, May 16, 2006) and amendment
39-14690 (71 FR 42021, July 25, 2006) and adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA-2008-0018; Directorate Identifier 2007-NM-
145-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by February
13, 2008.
Affected ADs
(b) This AD supersedes AD 2006-10-11 and AD 2006-15-10.
Applicability
(c) This AD applies to all Airbus Model A310 series airplanes
and A300-600 series airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (r) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued operational safety of the airplane. The FAA has
provided guidance for this determination in Advisory Circular (AC)
25-1529-1.
Unsafe Condition
(d) This AD results from the manufacturer's determination that
life limitations and maintenance tasks are necessary in order to
ensure continued operational safety of the affected airplanes. We
are issuing this AD to prevent reduced structural integrity of these
airplanes due to the failure of system components.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006-10-11
Inspection and Corrective Action
(f) For Airbus Model A310-203, -204, -221, -222, -304, -322, -
324, and -325 airplanes, except for airplanes on which Airbus
Modification 12247 has been embodied in production: At the earlier
of the compliance times specified in paragraph (f)(1) or (f)(2) of
this AD, perform a detailed inspection for stress corrosion cracking
of the flight transmission shafts located between the power control
unit (PCU) and the torque limiters in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-27-2092,
Revision 02, dated April 11, 2005. Thereafter, repeat the
inspections as required by paragraph (g) of this AD. Before further
flight, replace any cracked transmission shaft discovered during any
inspection required by this AD with a new or reconditioned shaft, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-27-2095, dated March 29, 2000. Doing an inspection in
accordance with paragraph (o) or (p) of this AD terminates the
requirements of this paragraph.
(1) Within 2,000 flight hours after the last flap asymmetry
protection test performed in accordance with Airbus A310 Maintenance
Planning Document (MPD) Task 275600-01-1.
(2) Within 8,000 flight cycles after the last flap asymmetry
protection test performed in accordance with Airbus A310 MPD Task
275600-02-1 or 800 flight cycles after June 20, 2006 (the effective
date of AD 2006-10-11), whichever comes later.
Note 2: Airbus Service Bulletin A310-27-2092, Revision 02, dated
April 11, 2005, refers to Lucas Liebherr Service Bulletin 551A-27-
624, Revision 1, dated August 18, 2000, as an additional source of
service information for accomplishing the inspections.
Note 3: Airbus Service Bulletin A310-27-2092, Revision 02,
refers to Airbus Service Bulletin A310-27-2095, dated March 29,
2000, as a source of service information for replacing the flap
transmission shafts.
Note 4: Airbus Service Bulletin A310-27-2095 refers to Lucas
Liebherr Service Bulletin 551A-27-M551-05, dated January 12, 2000,
as an additional source of service information for replacing the
flap transmission shafts.
Repetitive Inspections
(g) Repeat the inspection required by paragraph (f) of this AD
at the applicable times specified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD. Doing an inspection in accordance with paragraph
(o) or (p) of this AD terminates the requirements of this paragraph.
(1) Before further flight after any occurrence of jamming of the
flap transmission system.
(2) At intervals not to exceed 2,000 flight hours after each
flap asymmetry protection test performed in accordance with Airbus
A310 MPD Task 275600-01-1.
(3) At intervals not to exceed 8,000 flight cycles after each
flap asymmetry protection test performed in accordance with Airbus
A310 MPD Task 275600-02-1.
Optional Terminating Action
(h) Replacing any flap transmission shaft with a new or
reconditioned transmission shaft in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-27-2095,
dated March 29, 2000, ends the inspections required by paragraphs
(f) and (g) of this AD for that transmission shaft only.
Actions Performed Using Previously Issued Service Information
(i) Actions performed in accordance with Airbus Service Bulletin
A310-27-2092, dated April 9, 1999; or Revision 01, dated December
11, 2001; are considered acceptable for compliance with the
corresponding requirements of paragraphs (f) and (g) of this AD.
No Reporting
(j) Although Airbus Service Bulletin A310-27-2092, Revision 02,
dated April 11, 2005, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
Restatement of Requirements of AD 2006-15-10
Service Bulletin References
(k) Unless otherwise specified in this AD, the term ``service
bulletin,'' as used in paragraphs (l), (m), and (n) of this AD,
means the applicable required service bulletin identified in Table 1
of this AD. The service bulletins refer to Goodrich Actuation
Systems Service Bulletin 47142-27-11, Revision 3, dated April 25,
2005, as an additional source of service information for the
required actions.
[[Page 2200]]
Table 1.--Service Bulletins
------------------------------------------------------------------------
Approved Airbus
Service Bulletin
Required Airbus Service version for actions Airbus airplane
Bulletin done before the model
effective date of
this AD
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A300-27-6044, Revision 04, A300-27-6044, A300 B4-601, B4-603,
dated September 10, 2001. Revision 02, dated B4-620, and B4-622.
August 26, 2000; or A300 B4-605R and B4-
Revision 03, dated 622R.
June 28, 2001. A300 F4-605R and F4-
622R.
A300 C4-605R Variant
F.
A310-27-2089, Revision 02, A310-27-2089, A310-203, -204, -
dated June 28, 2001. Revision 01, dated 221, and -222.
August 25, 2000. A310-304, -322, -
324, and -325.
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Inspection
(l) At the applicable time specified in paragraph (l)(1) or
(l)(2) of this AD, do a detailed inspection of specified components
of the THSA in accordance with paragraph 1.E.(2)(a) and the
Accomplishment Instructions of the applicable service bulletin.
Repair any discrepancy before further flight in accordance with a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA) (or its delegated agent). TRW Aeronautical Systems/
Lucas Aerospace Component Maintenance Manual 27-44-13, dated
September 14, 2001, is one acceptable method for the repair. Doing
an inspection in accordance with paragraph (o) or (p) of this AD
terminates the requirements of this paragraph.
(1) If the flight hours accumulated on the THSA can be
positively determined: Inspect at the earlier of:
(i) Before the accumulation of 47,000 total flight hours on the
THSA, or within 600 flight hours after August 29, 2006 (the
effective date of AD 2006-15-10), whichever occurs later.
(ii) Within 25 years since the THSA was new or within 600 flight
hours after August 29, 2006, whichever occurs later.
(2) If the flight hours accumulated on the THSA cannot be
positively determined: Inspect before the accumulation of 47,000
total flight hours on the airplane, or within 600 flight hours after
August 29, 2006, whichever occurs later.
Note 5: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Follow-on Repetitive Tasks
(m) After the inspection required by paragraph (l) of this AD:
Do the repetitive tasks in accordance with the Accomplishment
Instructions and at the times specified in paragraph 1.E.(2)(b) of
the service bulletin, as applicable, except as provided by paragraph
(n) of this AD. The repetitive tasks are valid only until the THSA
operational life exceeds 65,000 flight hours, 40,000 flight cycles,
or 25 years, whichever occurs first. Before the THSA is operated
beyond these extended life goals, it must be replaced with a new
THSA, except as required by paragraph (n) of this AD. Doing an
inspection in accordance with paragraph (o) or (p) of this AD
terminates the requirements of this paragraph.
THSA Replacement
(n) For any THSA, whether discrepant or not, that is replaced
with a new THSA: Within 47,000 flight hours or 25 years, whichever
occurs first, after the THSA is replaced, do the applicable tasks
specified in paragraph 1.E.(2)(a) and the Accomplishment
Instructions of the applicable service bulletin. Thereafter repeat
the tasks within the repetitive intervals specified in paragraph
1.E.(2)(b) of the applicable service bulletin. Doing the
corresponding tasks in accordance with paragraph (o) or (p) of this
AD terminates the requirements of this paragraph.
New Requirements of This AD
Revise Airworthiness Limitations Section (ALS) to Incorporate
Limitations and Maintenance Tasks for Aging Systems Maintenance
(o) Within 3 months after the effective date of this AD, revise
the Airworthiness Limitations Section (ALS) of the Instructions for
Continued Airworthiness to incorporate Airbus A310 ALS Part 4--Aging
Systems Maintenance, Revision 01, dated December 21, 2006; and A300-
600 ALS Part 4--Aging Systems Maintenance, Revision 01, dated
December 21, 2006; as applicable. For all tasks identified in Airbus
A310 ALS Part 4--Aging Systems Maintenance, Revision 01; and A300-
600 ALS Part 4--Aging Systems Maintenance, Revision 01; the initial
compliance times start from the effective date of this AD, except as
provided by paragraph (p) of this AD. The repetitive inspections
must be accomplished thereafter at the interval specified in Airbus
A310 ALS Part 4--Aging Systems Maintenance, Revision 01; and A300-
600 ALS Part 4--Aging Systems Maintenance, Revision 01.
(p) For airplanes on which any life limitation/maintenance task
has been complied with in accordance with the requirements of AD
2006-10-11 or AD 2006-15-10, the last accomplishment of each
limitation/task must be retained as a starting point for the
accomplishment of each corresponding limitation/task interval now
introduced in Airbus A310 ALS Part 4--Aging Systems Maintenance,
Revision 01, dated December 21, 2006; and A300-600 ALS Part 4--Aging
Systems Maintenance, Revision 01, dated December 21, 2006; as
applicable.
(q) Except as provided by paragraph (r) of this AD: After
accomplishing the actions specified in paragraphs (o) and (p) of
this AD, no alternative inspection, inspection intervals, or
limitations may be used.
Alternative Methods of Compliance (AMOCs)
(r)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in accordance with AD 2006-10-11
are not approved as AMOCs with this AD.
(4) AMOCs approved previously in accordance with AD 2006-15-10
are not approved as AMOCs with this AD.
Related Information
(s) EASA airworthiness directive 2007-0092, dated April 10,
2007, also addresses the subject of this AD.
Issued in Renton, Washington, on January 3, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-380 Filed 1-11-08; 8:45 am]
BILLING CODE 4910-13-P
