Airworthiness Directives; Airbus Model A310-203 and -222 Airplanes and Model A300 B4-620 Airplanes, 21274-21278 [E9-10614]
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21274
Proposed Rules
Federal Register
Vol. 74, No. 87
Thursday, May 7, 2009
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0431; Directorate
Identifier 2007–NM–174–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310–203 and –222 Airplanes and
Model A300 B4–620 Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above that would
supersede an existing AD. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country to identify
and correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as:
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France AD 86–102–74(B) [which
corresponds to FAA AD 88–06–03,
amendment 39–5871] was issued to prevent
development of damage, which was
discovered during [a] fatigue test in the
attachment angles of the rear pressure
bulkhead (fuselage frame 80/82).
Following the life extension activities
linked to the A310 program, the interval of
inspection for A310–200 aircraft series was
reduced from 12000 flight cycles (FC) to 9000
FC * * *.
Some stress analysis conducted in the
frame of the life extension activities of the
A300–600 program leads the manufacturer to
reduce as well the interval of inspection
applicable to A300B4–620 and A300C4–620
aircraft models.
The unsafe condition is cracking in the
attachment angles of the rear pressure
bulkhead, which could result in failure
of the rear pressure bulkhead. The
proposed AD would require actions that
are intended to address the unsafe
condition described in the MCAI.
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DATES: We must receive comments on
this proposed AD by June 8, 2009.
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 W12–40, 1200 New Jersey
Avenue, SE., Washington, DC, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed 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 https://www.airbus.com. You
may review copies of the referenced
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.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office 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 Operations
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:
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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–2009–0431; Directorate Identifier
2007–NM–174–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 based on 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 March 3, 1988, we issued AD 88–
06–03, Amendment 39–5871 (53 FR
7730, March 10, 1988). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 88–06–03, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, advised that, due to life
extension activities linked to the A310
program and stress analysis conducted
in the frame of the life extension
activities of the A300–600 program, the
repetitive inspection interval for the
attachment angles of the rear pressure
bulkhead has been reduced from 12,000
flight cycles to 9,000 flight cycles for
Model A310–203 and –222 airplanes
and Model A300 B4–620 airplanes.
EASA has issued Airworthiness
Directive 2007–0297R1, dated
September 17, 2008 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France AD 86–102–74(B) [which
corresponds to FAA AD 88–06–03] was
issued to prevent development of damage,
which was discovered during [a] fatigue test
in the attachment angles of the rear pressure
bulkhead (fuselage frame 80/82).
Following the life extension activities
linked to the A310 program, the interval of
inspection for A310–200 aircraft series was
reduced from 12000 flight cycles (FC) to 9000
FC, which prompted the issuance of EASA
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AD 2007–0157, superseding DGAC France
AD 86–102–74(B).
Some stress analysis conducted in the
frame of the life extension activities of the
A300–600 program leads the manufacturer to
reduce as well the interval of inspection
applicable to A300B4–620 and A300C4–620
aircraft models.
EASA AD 2007–02977 superseded EASA
AD 2007–0157, retaining for A310 aircraft the
requirements of EASA AD 2007–0157 and
requiring the application of Airbus Service
Bulletin (SB) A300–53–6005 Revision 4 on
Airbus A300–600 aircraft, reducing the
inspection interval from 12000 FC to 9000
FC.
[EASA] AD [2007–0297] has been revised
to remove an inappropriate reference
regarding the normal inspection program
from the Compliance section, Note 3.
The unsafe condition is cracking in
the attachment angles of the rear
pressure bulkhead, which could result
in failure of the rear pressure bulkhead.
The required actions include a
modification of the rear pressure
bulkhead to improve the fatigue life of
the attachment angles at frame (FR) 80/
82, and, for certain airplanes, repetitive
inspections for cracks in the rear
pressure bulkhead and repair if
necessary.
The modification includes installing
additional attachment angles on the
circumference of FR 80/82; installing a
filler; installing additional supports
between the aft pressure bulkhead and
FR 80/82; installing an additional frame
stiffener and support between the aft
pressure bulkhead and FR 79 at stringer
(STGR) 13; modifying the aft lavatories;
applying surface protection to the
modified area of the aft pressure
bulkhead; modifying, reidentifying, and
installing the heat and sound insulation
in the area of STGR 9 and STGR 13 and
between FR 79 and FR 80/82, left and
right; and for certain airplanes, doing
related investigative and corrective
actions if necessary.
The related investigative action is
doing a visual inspection around the
entire circumference between FR 80/82
and the aft pressure bulkhead for
damaged filler. The corrective action is
removing any damaged filler and the
adjacent area around the damage.
We have removed Airbus Model
A310–221 airplanes having serial
numbers 295 and 0306 from the
applicability of this proposed AD. The
MCAI does not include Airbus Model
A310–221 in its applicability as it has
been determined that those airplanes are
not subject to the identified unsafe
condition addressed by the relevant
service information listed below.
However, those airplanes are subject to
certain other actions required by AD
2006–22–03, amendment 39–14800 (71
FR 62890, October 27, 2006), as
specified in the ‘‘Other Relevant
Rulemaking’’ paragraph below.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued the following
service bulletins:
• Airbus Service Bulletin A310–53–
2024, Revision 05, dated October 13,
2006.
• Airbus Service Bulletin A310–53–
2025, Revision 06, dated August 3,
2006.
• Airbus Service Bulletin A300–53–
6005, Revision 04, dated July 18, 2007.
• Airbus Service Bulletin A300–53–
6006, Revision 3, dated March 24, 1989.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
Other Relevant Rulemaking
We issued AD 2006–22–03 to prevent
corrosion on the inner rim angle and
cleat profile splice of the aft pressure
bulkhead. That AD applies to Airbus
Model A310 and A300–600 series
airplanes, except airplanes on which
Airbus Modification 6788 has been
incorporated in production. That AD
requires modification of the aft pressure
bulkhead for improved corrosion
protection and drainage, and a related
concurrent action.
The related concurrent action
specified in paragraph (h) of AD 2006–
22–03 is a modification of the aft
pressure bulkhead in accordance with
Airbus Service Bulletin A310–53–2025,
Revision 06, dated August 3, 2006, and
Airbus Service Bulletin A300–53–6006,
Revision 3, dated March 24, 1989, as
applicable (which is the same
modification that this NPRM would
require). The compliance time to do the
modification specified in paragraph (h)
of AD 2006–22–03 is prior to or
concurrent with the actions specified in
paragraph (g) of AD 2006–22–03; the
compliance time for paragraph (g) of AD
2006–22–03 is within 60 months after
December 1, 2006 (the effective date of
AD 2006–22–03). This NPRM would
supersede AD 2006–22–03 to require
that the modification of the aft pressure
bulkhead be done before the
accumulation of 12,000 total flight
cycles since first flight, or within 1,500
flight cycles, whichever occurs later.
Certain airplanes affected by AD
2006–22–03 are also affected by this
NPRM, and therefore, the requirements
of this NPRM would necessitate that
some operators do the modification
required by paragraph (h) of AD 2006–
22–03 early. Accomplishing the
modification within the compliance
time specified in paragraph (f)(2) of this
NPRM is necessary to address cracking
in the attachment angles of the rear
pressure bulkhead, which could result
in failure of the rear pressure bulkhead.
Other Corrosion and Fatigue ADs
Operators should note that we have
also issued other ADs that involve work
in the area of the aft pressure bulkhead.
We issued those ADs to address unsafe
conditions related to either corrosion or
fatigue in the aft pressure bulkhead. The
following table, titled ‘‘Other relevant
rulemaking,’’ provides an overview of
all those issued ADs.
TABLE—OTHER RELEVANT RULEMAKING
AD—
Refers to Airbus Service Bulletin—
Requiring—
Addressing—
88–06–03 (would be superseded by
this proposed AD).
A310–53–2024, Revision 1, dated June 20, 1986;
and Revision 3, February 17, 1987.
A310–53–2025, original issue, dated April 21,
1986; and Revision 3, April 7, 1987.
A300–53–6066, dated October 16, 1996; and Revision 01, dated March 11, 1998.
Repetitive inspections ...
Fatigue.
Modification ...................
Fatigue.
Repetitive inspections ...
Corrosion.
A310–53–2092, dated October 16, 1996; and Revision 01, dated March 11, 1998.
A300–53–6136, Revision 01, dated July 18, 2005
Repetitive inspections ...
Corrosion.
Repetitive inspections ...
Corrosion.
A310–53–2114, Revision 01, dated September 1,
2005.
Repetitive inspections ...
Corrosion.
98–19–22, amendment 39–10763 (63
FR 49656, September 17, 1998)
(superseded by AD 2005–26–16).
2005–26–16, amendment 39–14437
(70 FR 77307, December 30, 2005).
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TABLE—OTHER RELEVANT RULEMAKING—Continued
AD—
Refers to Airbus Service Bulletin—
Requiring—
Addressing—
2006–22–03, amendment 39–14800
(71 FR 62890, October 27, 2006).
A300–53–6017,
2004.
A310–53–2036,
2004.
A300–53–6006,
A310–53–2025,
Revision 02, dated February 25,
Modification ...................
Corrosion.
Revision 02, dated February 25,
Modification ...................
Corrosion.
Revision 3, March 24, 1989 .......
Revision 06, August 3, 2006 ......
Modification ...................
Modification ...................
Fatigue.
Fatigue.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a NOTE within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 32 products of U.S. registry.
We also estimate that it would take 668
work-hours per product to comply with
the basic requirements of this proposed
AD. The average labor rate is $80 per
work-hour. Required parts would cost
about $15,322 per product. Where the
service information lists required parts
costs that are covered under warranty,
we have assumed that there will be no
charge for these costs. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$2,200,384, or $68,762 per product.
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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 determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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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 FAA amends § 39.13 by
removing Amendment 39–5871 (53 FR
7730, March 10, 1988) and adding the
following new AD:
Airbus: Docket No. FAA–2009–0431;
Directorate Identifier 2007–NM–174–AD.
Comments Due Date
(a) We must receive comments by June 8,
2009.
Affected ADs
(b) The proposed AD supersedes AD 88–
06–03, Amendment 39–5871.
Applicability
(c) This AD applies to Airbus Model A310–
203 and –222 airplanes, and Model A300 B4–
620 airplanes; certificated in any category; all
serial numbers except airplanes on which
Airbus Modification 05526 has been
incorporated in production.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
´ ´
DGAC (Direction Generale de l’Aviation
Civile) France AD 86–102–74(B) [which
corresponds to FAA AD 88–06–03,
amendment 39–5871] was issued to prevent
development of damage, which was
discovered during [a] fatigue test in the
attachment angles of the rear pressure
bulkhead (fuselage frame 80/82).
Following the life extension activities
linked to the A310 program, the interval of
inspection for A310–200 aircraft series was
reduced from 12000 flight cycles (FC) to 9000
FC, which prompted the issuance of EASA
AD 2007–0157, superseding DGAC France
AD 86–102–74(B).
Some stress analysis conducted in the
frame of the life extension activities of the
A300–600 program leads the manufacturer to
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reduce as well the interval of inspection
applicable to A300B4–620 and A300C4–620
aircraft models.
EASA AD 2007–0297 superseded EASA
AD 2007–0157, retaining for A310 aircraft the
requirements of EASA AD 2007–0157 and
requiring the application of Airbus Service
Bulletin (SB) A300–53–6005 Revision 4 on
Airbus A300–600 aircraft, reducing the
inspection interval from 12000 FC to 9000
FC.
[EASA] AD [2007–0297] has been revised
to remove an inappropriate reference
regarding the normal inspection program
from the Compliance section, Note 3.
The unsafe condition is cracking in the
attachment angles of the rear pressure
bulkhead, which could result in failure of the
rear pressure bulkhead. The required actions
include a modification of the rear pressure
bulkhead to improve the fatigue life of the
attachment angles at frame (FR) 80/82;
applicable related investigative and
corrective actions; and, for certain airplanes,
repetitive inspections for cracks in the rear
pressure bulkhead and repair if necessary.
Requirements of This AD: Actions and
Compliance
(f) Unless already done, do the following
actions.
Modification
(1) Except as required by paragraph (f)(2)
of this AD: Before the accumulation of 12,000
total flight cycles since first flight, or within
1,500 flight cycles after the effective date of
this AD, whichever occurs later, modify the
aft pressure bulkhead to improve the fatigue
life of the attachment angles at frame 80/82
and do all applicable related investigative
and corrective actions, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A300–53–6006, Revision 3,
dated March 24, 1989; or Airbus Service
Bulletin A310–53–2025, Revision 06, dated
August 3, 2006; as applicable. Do all
applicable related investigative and
corrective actions before further flight.
(2) For airplanes identified in paragraph (c)
of AD 2006–22–03, amendment 39–14800: At
the earlier of the compliance times specified
in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD,
do the actions specified in paragraph (f)(1) of
this AD.
(i) Before the accumulation of 12,000 total
flight cycles since first flight, or within 1,500
flight cycles after the effective date of this
AD, whichever occurs later.
(ii) At the compliance time specified in
paragraph (h) of AD 2006–22–03.
Inspections and Corrective Action
(3) For airplanes on which the
modification required by paragraph (f)(1) or
(f)(2) of this AD is done after the
accumulation of 6,000 total flight cycles
since first flight: At the times specified in
paragraphs (f)(3)(i) and (f)(3)(ii) of this AD,
do an eddy current inspection for any
cracking in the critical area of the rear
pressure bulkhead between stringers 8 and
18, and repair all cracking before further
flight, in accordance with the
Accomplishment Instructions of Airbus
A300–53–6005, Revision 04, dated July 18,
2007; or Airbus Service Bulletin A310–53–
2024, Revision 05, dated October 13, 2006; as
applicable.
(i) Before or concurrently with the
modification required by paragraph (f)(1) or
(f)(2) of this AD, as applicable; and
(ii) Before the accumulation of 18,000 total
flight cycles since first flight, or within 1,500
flight cycles after the effective date of this
AD, whichever occurs later; and thereafter at
intervals not to exceed 9,000 flight cycles.
(4) For airplanes on which the
modification required by paragraph (f)(1) or
(f)(2) of this AD is done at or before the
accumulation of 6,000 total flight cycles
since first flight: Before the accumulation of
18,000 total flight cycles since first flight, or
within 1,500 flight cycles after the effective
date of this AD, whichever occurs later, do
an eddy current inspection for any cracking
in the critical area of the rear pressure
bulkhead between stringers 8 and 18, and
repair all cracking before further flight, in
accordance with the Accomplishment
Instructions of Airbus A300–53–6005,
Revision 04, dated July 18, 2007; or Airbus
Service Bulletin A310–53–2024, Revision 05,
dated October 13, 2006; as applicable. Repeat
the inspection thereafter at intervals not to
exceed 9,000 flight cycles.
(5) Modifications done before the effective
date of this AD in accordance with the
service bulletins identified in Table 1 of this
AD are acceptable for compliance with the
requirements of paragraph (f)(1) and (f)(2) of
this AD.
TABLE 1—MODIFICATIONS DONE USING PREVIOUS SERVICE BULLETINS
Airbus Service
Bulletin
Model
A300 B4–620 airplanes ...........................................................
A310–203 and –222 airplanes ................................................
(6) Inspections done before the effective
date of this AD in accordance with the
service bulletins identified in Table 2 of this
A300–53–6006
A300–53–6006
A300–53–6006
A310–53–2025
A310–53–2025
A310–53–2025
A310–53–2025
A310–53–2025
A310–53–2025
Revision
Dated
Original ...................................
1 ..............................................
2 ..............................................
Original ...................................
1 ..............................................
2 ..............................................
3 ..............................................
4 ..............................................
5 ..............................................
May 6, 1986.
September 19, 1986.
August 11, 1988.
April 21, 1986.
September 19, 1986.
February 16, 1987.
April 7, 1987.
October 20, 1987.
March 24, 1989.
AD are acceptable for compliance with the
requirements of paragraph (f)(3) of this AD.
TABLE 2—INSPECTIONS DONE WITH PREVIOUS SERVICE BULLETINS
Airbus Service
Bulletin
Model
A300 B4–620 airplanes ...........................................................
A310–203 and –222 airplanes ................................................
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A300–53–6005
A300–53–6005
A300–53–6005
A300–53–6005
A310–53–2024
A310–53–2024
A310–53–2024
A310–53–2024
A310–53–2024
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Revision
Dated
Original ...................................
1 ..............................................
2 ..............................................
3 ..............................................
Original ...................................
1 ..............................................
2 ..............................................
3 ..............................................
4 ..............................................
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May 6, 1986.
June 20, 1986.
September 22, 1986.
April 22, 1987.
April 21, 1986.
June 20, 1986.
October 2, 1986.
February 17, 1987.
February 2, 1988.
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(7) Modification of the aft pressure
bulkhead to improve the fatigue life of the
attachment angles at frame (FR) 80/82 in
accordance with paragraph (h) of AD 2006–
22–03, is acceptable for compliance with the
corresponding requirement of paragraphs
(f)(1) and (f)(2) of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: This
AD includes a compliance time specified in
paragraph (f)(2) of this AD for airplanes that
are also affected by AD 2006–22–03. We
realize that the requirements of this AD will
necessitate that some operators do the
modification required by paragraph (h) of AD
2006–22–03 early. However, accomplishing
the modification within the compliance time
specified in this AD is required to address
cracking in the attachment angles of the rear
pressure bulkhead, which could result in
failure of the rear pressure bulkhead.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Stafford,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1622; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2007–0297R1, dated September 17,
2008, and the service bulletins listed in Table
3 of this AD, for related information.
TABLE 3—RELATED SERVICE BULLETINS
Airbus Service Bulletin
A310-53-2024
A310-53-2025
A300-53-6005
A300-53-6006
........................................................................................................................................
........................................................................................................................................
........................................................................................................................................
........................................................................................................................................
Issued in Renton, Washington, on May 1,
2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–10614 Filed 5–6–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0429; Directorate
Identifier 2007–NM–059–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–300 and 737–400 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Boeing Model 737–300 and 737–400
series airplanes. This proposed AD
would require repetitive inspections to
detect cracking of the aft fuselage skin,
and related investigative/corrective
actions if necessary. This proposed AD
results from reports of cracks in the aft
fuselage skin on both sides of the
airplane. We are proposing this AD to
VerDate Nov<24>2008
Revision
16:34 May 06, 2009
Jkt 217001
detect and correct cracking in the aft
fuselage skin along the longitudinal
edges of the bonded skin doubler, which
could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by June 22, 2009.
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 Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207;
telephone 206–544–5000, extension 1,
fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
Date
05
06
04
3
October 13, 2006.
August 3, 2006.
July 18, 2007.
March 24, 1989.
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221 or 425–227–1152.
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:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6447; fax (425) 917–6590.
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–2009–0429; Directorate Identifier
2007–NM–059–AD’’ at the beginning of
E:\FR\FM\07MYP1.SGM
07MYP1
]]>Agencies
[Federal Register Volume 74, Number 87 (Thursday, May 7, 2009)]
[Proposed Rules]
[Pages 21274-21278]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-10614]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 74, No. 87 / Thursday, May 7, 2009 / Proposed
Rules
[[Page 21274]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0431; Directorate Identifier 2007-NM-174-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-203 and -222
Airplanes and Model A300 B4-620 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated by an aviation authority of another country to
identify and correct an unsafe condition on an aviation product. The
MCAI describes the unsafe condition as:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03,
amendment 39-5871] was issued to prevent development of damage,
which was discovered during [a] fatigue test in the attachment
angles of the rear pressure bulkhead (fuselage frame 80/82).
Following the life extension activities linked to the A310
program, the interval of inspection for A310-200 aircraft series was
reduced from 12000 flight cycles (FC) to 9000 FC * * *.
Some stress analysis conducted in the frame of the life
extension activities of the A300-600 program leads the manufacturer
to reduce as well the interval of inspection applicable to A300B4-
620 and A300C4-620 aircraft models.
The unsafe condition is cracking in the attachment angles of the rear
pressure bulkhead, which could result in failure of the rear pressure
bulkhead. The proposed AD would require actions that are intended to
address the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by June 8, 2009.
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 W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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 https://www.airbus.com. You may review copies of the referenced 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
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 Operations 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-2009-0431;
Directorate Identifier 2007-NM-174-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 based on 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 March 3, 1988, we issued AD 88-06-03, Amendment 39-5871 (53 FR
7730, March 10, 1988). That AD required actions intended to address an
unsafe condition on the products listed above.
Since we issued AD 88-06-03, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, advised that, due to life extension activities
linked to the A310 program and stress analysis conducted in the frame
of the life extension activities of the A300-600 program, the
repetitive inspection interval for the attachment angles of the rear
pressure bulkhead has been reduced from 12,000 flight cycles to 9,000
flight cycles for Model A310-203 and -222 airplanes and Model A300 B4-
620 airplanes.
EASA has issued Airworthiness Directive 2007-0297R1, dated
September 17, 2008 (referred to after this as ``the MCAI''), to correct
an unsafe condition for the specified products. The MCAI states:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03] was
issued to prevent development of damage, which was discovered during
[a] fatigue test in the attachment angles of the rear pressure
bulkhead (fuselage frame 80/82).
Following the life extension activities linked to the A310
program, the interval of inspection for A310-200 aircraft series was
reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the
issuance of EASA
[[Page 21275]]
AD 2007-0157, superseding DGAC France AD 86-102-74(B).
Some stress analysis conducted in the frame of the life
extension activities of the A300-600 program leads the manufacturer
to reduce as well the interval of inspection applicable to A300B4-
620 and A300C4-620 aircraft models.
EASA AD 2007-02977 superseded EASA AD 2007-0157, retaining for
A310 aircraft the requirements of EASA AD 2007-0157 and requiring
the application of Airbus Service Bulletin (SB) A300-53-6005
Revision 4 on Airbus A300-600 aircraft, reducing the inspection
interval from 12000 FC to 9000 FC.
[EASA] AD [2007-0297] has been revised to remove an
inappropriate reference regarding the normal inspection program from
the Compliance section, Note 3.
The unsafe condition is cracking in the attachment angles of the
rear pressure bulkhead, which could result in failure of the rear
pressure bulkhead. The required actions include a modification of the
rear pressure bulkhead to improve the fatigue life of the attachment
angles at frame (FR) 80/82, and, for certain airplanes, repetitive
inspections for cracks in the rear pressure bulkhead and repair if
necessary.
The modification includes installing additional attachment angles
on the circumference of FR 80/82; installing a filler; installing
additional supports between the aft pressure bulkhead and FR 80/82;
installing an additional frame stiffener and support between the aft
pressure bulkhead and FR 79 at stringer (STGR) 13; modifying the aft
lavatories; applying surface protection to the modified area of the aft
pressure bulkhead; modifying, reidentifying, and installing the heat
and sound insulation in the area of STGR 9 and STGR 13 and between FR
79 and FR 80/82, left and right; and for certain airplanes, doing
related investigative and corrective actions if necessary.
The related investigative action is doing a visual inspection
around the entire circumference between FR 80/82 and the aft pressure
bulkhead for damaged filler. The corrective action is removing any
damaged filler and the adjacent area around the damage.
We have removed Airbus Model A310-221 airplanes having serial
numbers 295 and 0306 from the applicability of this proposed AD. The
MCAI does not include Airbus Model A310-221 in its applicability as it
has been determined that those airplanes are not subject to the
identified unsafe condition addressed by the relevant service
information listed below. However, those airplanes are subject to
certain other actions required by AD 2006-22-03, amendment 39-14800 (71
FR 62890, October 27, 2006), as specified in the ``Other Relevant
Rulemaking'' paragraph below.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued the following service bulletins:
Airbus Service Bulletin A310-53-2024, Revision 05, dated
October 13, 2006.
Airbus Service Bulletin A310-53-2025, Revision 06, dated
August 3, 2006.
Airbus Service Bulletin A300-53-6005, Revision 04, dated
July 18, 2007.
Airbus Service Bulletin A300-53-6006, Revision 3, dated
March 24, 1989.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
Other Relevant Rulemaking
We issued AD 2006-22-03 to prevent corrosion on the inner rim angle
and cleat profile splice of the aft pressure bulkhead. That AD applies
to Airbus Model A310 and A300-600 series airplanes, except airplanes on
which Airbus Modification 6788 has been incorporated in production.
That AD requires modification of the aft pressure bulkhead for improved
corrosion protection and drainage, and a related concurrent action.
The related concurrent action specified in paragraph (h) of AD
2006-22-03 is a modification of the aft pressure bulkhead in accordance
with Airbus Service Bulletin A310-53-2025, Revision 06, dated August 3,
2006, and Airbus Service Bulletin A300-53-6006, Revision 3, dated March
24, 1989, as applicable (which is the same modification that this NPRM
would require). The compliance time to do the modification specified in
paragraph (h) of AD 2006-22-03 is prior to or concurrent with the
actions specified in paragraph (g) of AD 2006-22-03; the compliance
time for paragraph (g) of AD 2006-22-03 is within 60 months after
December 1, 2006 (the effective date of AD 2006-22-03). This NPRM would
supersede AD 2006-22-03 to require that the modification of the aft
pressure bulkhead be done before the accumulation of 12,000 total
flight cycles since first flight, or within 1,500 flight cycles,
whichever occurs later.
Certain airplanes affected by AD 2006-22-03 are also affected by
this NPRM, and therefore, the requirements of this NPRM would
necessitate that some operators do the modification required by
paragraph (h) of AD 2006-22-03 early. Accomplishing the modification
within the compliance time specified in paragraph (f)(2) of this NPRM
is necessary to address cracking in the attachment angles of the rear
pressure bulkhead, which could result in failure of the rear pressure
bulkhead.
Other Corrosion and Fatigue ADs
Operators should note that we have also issued other ADs that
involve work in the area of the aft pressure bulkhead. We issued those
ADs to address unsafe conditions related to either corrosion or fatigue
in the aft pressure bulkhead. The following table, titled ``Other
relevant rulemaking,'' provides an overview of all those issued ADs.
Table--Other Relevant Rulemaking
----------------------------------------------------------------------------------------------------------------
Refers to Airbus Service
AD-- Bulletin-- Requiring-- Addressing--
----------------------------------------------------------------------------------------------------------------
88-06-03 (would be superseded by A310-53-2024, Revision 1, Repetitive inspections Fatigue.
this proposed AD). dated June 20, 1986; and
Revision 3, February 17,
1987.
A310-53-2025, original Modification.......... Fatigue.
issue, dated April 21,
1986; and Revision 3,
April 7, 1987.
98-19-22, amendment 39-10763 (63 FR A300-53-6066, dated October Repetitive inspections Corrosion.
49656, September 17, 1998) 16, 1996; and Revision 01,
(superseded by AD 2005-26-16). dated March 11, 1998.
A310-53-2092, dated October Repetitive inspections Corrosion.
16, 1996; and Revision 01,
dated March 11, 1998.
2005-26-16, amendment 39-14437 (70 A300-53-6136, Revision 01, Repetitive inspections Corrosion.
FR 77307, December 30, 2005). dated July 18, 2005.
A310-53-2114, Revision 01, Repetitive inspections Corrosion.
dated September 1, 2005.
[[Page 21276]]
2006-22-03, amendment 39-14800 (71 A300-53-6017, Revision 02, Modification.......... Corrosion.
FR 62890, October 27, 2006). dated February 25, 2004.
A310-53-2036, Revision 02, Modification.......... Corrosion.
dated February 25, 2004.
A300-53-6006, Revision 3, Modification.......... Fatigue.
March 24, 1989.
A310-53-2025, Revision 06, Modification.......... Fatigue.
August 3, 2006.
----------------------------------------------------------------------------------------------------------------
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 32 products of U.S. registry. We also estimate that
it would take 668 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Required parts would cost about $15,322 per product. Where
the service information lists required parts costs that are covered
under warranty, we have assumed that there will be no charge for these
costs. As we do not control warranty coverage for affected parties,
some parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $2,200,384, or $68,762 per product.
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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 FAA amends Sec. 39.13 by removing Amendment 39-5871 (53 FR
7730, March 10, 1988) and adding the following new AD:
Airbus: Docket No. FAA-2009-0431; Directorate Identifier 2007-NM-
174-AD.
Comments Due Date
(a) We must receive comments by June 8, 2009.
Affected ADs
(b) The proposed AD supersedes AD 88-06-03, Amendment 39-5871.
Applicability
(c) This AD applies to Airbus Model A310-203 and -222 airplanes,
and Model A300 B4-620 airplanes; certificated in any category; all
serial numbers except airplanes on which Airbus Modification 05526
has been incorporated in production.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
DGAC (Direction G[eacute]n[eacute]rale de l'Aviation Civile)
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03,
amendment 39-5871] was issued to prevent development of damage,
which was discovered during [a] fatigue test in the attachment
angles of the rear pressure bulkhead (fuselage frame 80/82).
Following the life extension activities linked to the A310
program, the interval of inspection for A310-200 aircraft series was
reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the
issuance of EASA AD 2007-0157, superseding DGAC France AD 86-102-
74(B).
Some stress analysis conducted in the frame of the life
extension activities of the A300-600 program leads the manufacturer
to
[[Page 21277]]
reduce as well the interval of inspection applicable to A300B4-620
and A300C4-620 aircraft models.
EASA AD 2007-0297 superseded EASA AD 2007-0157, retaining for
A310 aircraft the requirements of EASA AD 2007-0157 and requiring
the application of Airbus Service Bulletin (SB) A300-53-6005
Revision 4 on Airbus A300-600 aircraft, reducing the inspection
interval from 12000 FC to 9000 FC.
[EASA] AD [2007-0297] has been revised to remove an
inappropriate reference regarding the normal inspection program from
the Compliance section, Note 3.
The unsafe condition is cracking in the attachment angles of the
rear pressure bulkhead, which could result in failure of the rear
pressure bulkhead. The required actions include a modification of
the rear pressure bulkhead to improve the fatigue life of the
attachment angles at frame (FR) 80/82; applicable related
investigative and corrective actions; and, for certain airplanes,
repetitive inspections for cracks in the rear pressure bulkhead and
repair if necessary.
Requirements of This AD: Actions and Compliance
(f) Unless already done, do the following actions.
Modification
(1) Except as required by paragraph (f)(2) of this AD: Before
the accumulation of 12,000 total flight cycles since first flight,
or within 1,500 flight cycles after the effective date of this AD,
whichever occurs later, modify the aft pressure bulkhead to improve
the fatigue life of the attachment angles at frame 80/82 and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-6006, Revision 3, dated March 24, 1989; or Airbus
Service Bulletin A310-53-2025, Revision 06, dated August 3, 2006; as
applicable. Do all applicable related investigative and corrective
actions before further flight.
(2) For airplanes identified in paragraph (c) of AD 2006-22-03,
amendment 39-14800: At the earlier of the compliance times specified
in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do the actions
specified in paragraph (f)(1) of this AD.
(i) Before the accumulation of 12,000 total flight cycles since
first flight, or within 1,500 flight cycles after the effective date
of this AD, whichever occurs later.
(ii) At the compliance time specified in paragraph (h) of AD
2006-22-03.
Inspections and Corrective Action
(3) For airplanes on which the modification required by
paragraph (f)(1) or (f)(2) of this AD is done after the accumulation
of 6,000 total flight cycles since first flight: At the times
specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, do an
eddy current inspection for any cracking in the critical area of the
rear pressure bulkhead between stringers 8 and 18, and repair all
cracking before further flight, in accordance with the
Accomplishment Instructions of Airbus A300-53-6005, Revision 04,
dated July 18, 2007; or Airbus Service Bulletin A310-53-2024,
Revision 05, dated October 13, 2006; as applicable.
(i) Before or concurrently with the modification required by
paragraph (f)(1) or (f)(2) of this AD, as applicable; and
(ii) Before the accumulation of 18,000 total flight cycles since
first flight, or within 1,500 flight cycles after the effective date
of this AD, whichever occurs later; and thereafter at intervals not
to exceed 9,000 flight cycles.
(4) For airplanes on which the modification required by
paragraph (f)(1) or (f)(2) of this AD is done at or before the
accumulation of 6,000 total flight cycles since first flight: Before
the accumulation of 18,000 total flight cycles since first flight,
or within 1,500 flight cycles after the effective date of this AD,
whichever occurs later, do an eddy current inspection for any
cracking in the critical area of the rear pressure bulkhead between
stringers 8 and 18, and repair all cracking before further flight,
in accordance with the Accomplishment Instructions of Airbus A300-
53-6005, Revision 04, dated July 18, 2007; or Airbus Service
Bulletin A310-53-2024, Revision 05, dated October 13, 2006; as
applicable. Repeat the inspection thereafter at intervals not to
exceed 9,000 flight cycles.
(5) Modifications done before the effective date of this AD in
accordance with the service bulletins identified in Table 1 of this
AD are acceptable for compliance with the requirements of paragraph
(f)(1) and (f)(2) of this AD.
Table 1--Modifications Done Using Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model Bulletin Revision Dated
----------------------------------------------------------------------------------------------------------------
A300 B4-620 airplanes............ A300-53-6006 Original........... May 6, 1986.
A300-53-6006 1.................. September 19, 1986.
A300-53-6006 2.................. August 11, 1988.
A310-203 and -222 airplanes...... A310-53-2025 Original........... April 21, 1986.
A310-53-2025 1.................. September 19, 1986.
A310-53-2025 2.................. February 16, 1987.
A310-53-2025 3.................. April 7, 1987.
A310-53-2025 4.................. October 20, 1987.
A310-53-2025 5.................. March 24, 1989.
----------------------------------------------------------------------------------------------------------------
(6) Inspections done before the effective date of this AD in
accordance with the service bulletins identified in Table 2 of this
AD are acceptable for compliance with the requirements of paragraph
(f)(3) of this AD.
Table 2--Inspections Done With Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service
Model Bulletin Revision Dated
----------------------------------------------------------------------------------------------------------------
A300 B4-620 airplanes............ A300-53-6005 Original........... May 6, 1986.
A300-53-6005 1.................. June 20, 1986.
A300-53-6005 2.................. September 22, 1986.
A300-53-6005 3.................. April 22, 1987.
A310-203 and -222 airplanes...... A310-53-2024 Original........... April 21, 1986.
A310-53-2024 1.................. June 20, 1986.
A310-53-2024 2.................. October 2, 1986.
A310-53-2024 3.................. February 17, 1987.
A310-53-2024 4.................. February 2, 1988.
----------------------------------------------------------------------------------------------------------------
[[Page 21278]]
(7) Modification of the aft pressure bulkhead to improve the
fatigue life of the attachment angles at frame (FR) 80/82 in
accordance with paragraph (h) of AD 2006-22-03, is acceptable for
compliance with the corresponding requirement of paragraphs (f)(1)
and (f)(2) of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: This AD includes a compliance time specified in
paragraph (f)(2) of this AD for airplanes that are also affected by
AD 2006-22-03. We realize that the requirements of this AD will
necessitate that some operators do the modification required by
paragraph (h) of AD 2006-22-03 early. However, accomplishing the
modification within the compliance time specified in this AD is
required to address cracking in the attachment angles of the rear
pressure bulkhead, which could result in failure of the rear
pressure bulkhead.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN: Tom
Stafford, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 2007-0297R1,
dated September 17, 2008, and the service bulletins listed in Table
3 of this AD, for related information.
Table 3--Related Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
A310[dash]53[dash]2024......................... 05 October 13, 2006.
A310[dash]53[dash]2025......................... 06 August 3, 2006.
A300[dash]53[dash]6005......................... 04 July 18, 2007.
A300[dash]53[dash]6006......................... 3 March 24, 1989.
----------------------------------------------------------------------------------------------------------------
Issued in Renton, Washington, on May 1, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-10614 Filed 5-6-09; 8:45 am]
BILLING CODE 4910-13-P
