Airworthiness Directives; Airbus Model A310-203 and -222 Airplanes and Model A300 B4-620 Airplanes, 49805-49809 [E9-23094]
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Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations
FAA AD Differences
2009–20–04 Glaser-Dirks Flugzeugbau
Gmbh: Amendment 39–16027; Docket
No. FAA–2009–0881; Directorate
Identifier 2009–CE–050–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 19, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model DG–100
gliders, serial numbers 5 and 21 through 103,
certificated in any category.
Subject
(d) Air Transport Association of America
(ATA) Code 27: Flight Controls.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
The Elevator control bearing stand RU19
was required to be inspected for correct
production in 1978 in accordance with
Technical Note (TN) No. 301/6. In 2009, an
accident occurred with a DG–100. The
suspension bolt was found torn out of the
bearing stand making the elevator
uncontrollable. The investigation confirmed
that the bearing stand had not been produced
correctly. It is therefore assumed that the
inspections per TN 301/6 did not produce
reliable results.
As a consequence, this new Airworthiness
Directive (AD) mandates replacement of the
bearing stand with a reinforced version.
CPrice-Sewell on DSKGBLS3C1PROD with RULES
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Before further flight after October 19,
2009 (the effective date of this AD), inspect
the bearing stand RU19 following paragraph
1 of the Instructions section of DG
Flugzeugbau Technical note No. 301/26, Rev.
1, dated August 4, 2009. You may take credit
for this paragraph if the bearing stand was
inspected before October 19, 2009 (the
effective date of this AD) following DG
Flugzeugbau Technical note No. 301/26,
dated July 16, 2009.
(2) If any discrepancy is found (crack,
delamination, etc.), before further flight
replace the bearing stand RU19 following
paragraph 3 of the Instructions section of DG
Flugzeugbau Technical note No. 301/26, Rev.
1, dated August 4, 2009.
(3) Within 3 months after October 19, 2009
(the effective date of this AD) replace the
bearing stand RU19 following paragraph 3 of
the Instructions section of DG Flugzeugbau
Technical note No. 301/26, Rev. 1, dated
August 4, 2009. You may take credit for this
paragraph if the bearing stand RU19 has been
replaced before October 19, 2009 (the
effective date of this AD) following DG
Flugzeugbau Technical note No. 301/6, dated
May 29, 1978, or following paragraph 3 of the
Instructions section of DG Flugzeugbau
Technical note No. 301/26, dated July 16,
2009.
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Note: This AD differs from the MCAI and/
or service information as follows:
(1) DG Flugzeugbau GmbH Technical Note
No. 301/26, Rev. 1, dated August 4, 2009,
states that instruction 1 may be executed by
the pilot/owner. By FAA regulations, this AD
requires all affected gliders to have the
required actions done by an appropriately
rated mechanic.
(2) The MCAI states to do the actions
following DG Flugzeugbau GmbH Technical
Note No. 301/26, dated July 16, 2009. DG
Flugzeugbau GmbH updated the technical
note after the MCAI was issued. We are
requiring you use the updated technical note
(DG Flugzeugbau GmbH Technical Note No.
301/26, Rev. 1, dated August 4, 2009) to do
the actions of this AD, unless the AD
specifies otherwise.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
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: Greg Davison, Glider Program
Manager, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4130; fax: (816)
329–4090. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) 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
(44 U.S.C. 3501 et.seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
49805
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact DG Flugzeugbau GmbH,
Otto-Lilienthal-Weg 2, 76646 Bruchsal,
Federal Republic of Germany; telephone:
+ 49 (0) 7251 3020140; Fax: +49 (0) 7251
3020149; Internet: https://www.dgflugzeugbau.de/index-e.html; E-Mail:
dirks@dg-flugzeugbau.de.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_
locations.html.
Issued in Kansas City, Missouri, on
September 17, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9–23047 Filed 9–28–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0431; Directorate
Identifier 2007–NM–174–AD; Amendment
39–16029; AD 2009–20–06]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310–203 and –222 Airplanes and
Model A300 B4–620 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Emergency AD No.:
2009–0163–E, dated July 29, 2009, DG
Flugzeugbau GmbH Technical Note No. 301/
26, dated July 16, 2009; DG Flugzeugbau
GmbH Technical Note No. 301/26, Rev. 1,
dated August 4, 2009; and DG Flugzeugbau
Technical note No. 301/6, dated May 29,
1978, for related information.
SUMMARY: We are superseding an
existing airworthiness directive (AD) for
the products listed above. This 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:
Material Incorporated by Reference
(i) You must use DG Flugzeugbau GmbH
Technical Note No. 301/26, Rev. 1, dated
August 4, 2009, to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
´ ´
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).
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Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations
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. We are
issuing this AD to require actions to
correct the unsafe condition on these
products.
DATES: This AD becomes effective
November 3, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 3, 2009.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
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:
CPrice-Sewell on DSKGBLS3C1PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on May 7, 2009 (74 FR 21274),
and proposed to supersede AD 88–06–
03, Amendment 39–5871 (53 FR 7730,
March 10, 1988). That NPRM proposed
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
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
VerDate Nov<24>2008
15:02 Sep 28, 2009
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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 2007–0297 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, 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.
You may obtain further information
by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request To Revise Paragraph (f)(4) of
the NPRM
Airbus requests that we revise
paragraph (f)(4) of the NPRM. Airbus
states that for the airplanes identified in
paragraph (f)(4) of the NPRM, it is not
necessary to do the actions in
accordance with the service bulletins
specified in paragraph (f)(4) of the
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NPRM. Airbus further states that those
airplanes are affected by Airworthiness
Limitation Item (ALI) Task 531919–01–
1A, as specified in the service bulletins
identified in paragraph (f)(4) of this AD
and the MCAI.
We agree with the commenter. The
actions specified in paragraph (f)(4) of
the NPRM are not required for the
airplanes identified in that paragraph
because those airplanes are already
inspected in accordance with ALI Task
531919–01–1A, and no additional
actions are necessary. We have
confirmed with EASA that this is the
intent of the MCAI. We have removed
paragraph (f)(4) of the NPRM as it is
unnecessary, and added a new Note 1 to
this AD to clarify that no action is
required by this AD for the airplanes
discussed in this paragraph. We have reidentified the subsequent paragraphs
accordingly.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
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 required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
about 32 products of U.S. registry. We
also estimate that it will take about 668
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will 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
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Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations
higher than estimated here. Based on
these figures, we estimate the cost of
this AD to the U.S. operators to be
$2,200,384, or $68,762 per product.
section. Comments will be available in
the AD docket shortly after receipt.
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 AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
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 AD and placed it in the AD docket.
CPrice-Sewell on DSKGBLS3C1PROD with RULES
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 the NPRM, 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
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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]
49807
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.
2. The FAA amends § 39.13 by
removing Amendment 39–5871 (53 FR
7730, March 10, 1988) and adding the
following new AD:
Requirements of This AD: Actions and
Compliance
(f) Unless already done, do the following
actions.
2009–20–06 Airbus: Amendment 39–16029.
Docket No. FAA–2009–0431; Directorate
Identifier 2007–NM–174–AD.
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 Mandatory
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.
■
Effective Date
(a) This airworthiness directive (AD)
becomes effective November 3, 2009.
Affected ADs
(b) This 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
reduce as well the interval of inspection
applicable to A300B4–620 and A300C4–620
aircraft models.
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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
Mandatory Service Bulletin A300–53–6005,
Revision 04, dated July 18, 2007; or Airbus
Mandatory Service Bulletin A310–53–2024,
Revision 05, dated October 13, 2006; as
applicable.
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(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.
Note 1: 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: No action is required by this
AD. For these airplanes, refer to Airbus
A300–600 ALI Task 531919–01–1A or Airbus
A310 ALI Task 531919–01–1A, as applicable,
for guidance on the normal inspection
program.
(4) 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
Model—
Airbus Service Bulletin—
Revision—
Dated—
A300 B4–620 airplanes ....................................
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
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.
A310–203 and –222 airplanes .........................
(5) 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
Model—
Airbus Service Bulletin—
Revision—
A300 B4–620 airplanes ....................................
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
Original ......................
1 ................................
2 ................................
3 ................................
Original ......................
1 ................................
2 ................................
3 ................................
4 ................................
A310–203 and –222 airplanes .........................
(6) 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.
CPrice-Sewell on DSKGBLS3C1PROD with RULES
FAA AD Differences
Note 2: 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.
Dated—
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.
(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
Airbus Mandatory Service Bulletin A300–53–6005 .....................................................................................
Airbus Mandatory Service Bulletin A310–53–2024 .....................................................................................
Airbus Mandatory Service Bulletin A310–53–2025 .....................................................................................
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04
05
06
29SER1
July 18, 2007.
October 13, 2006.
August 3, 2006.
49809
Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations
TABLE 3—RELATED SERVICE BULLETINS—Continued
Airbus Service Bulletin
Revision
Airbus Service Bulletin A300–53–6006 .......................................................................................................
Material Incorporated by Reference
(i) You must use the service information
contained in Table 4 of this AD to do the
Date
3
March 24, 1989.
actions required by this AD, unless the AD
specifies otherwise.
TABLE 4—MATERIAL INCORPORATED BY REFERENCE
Airbus Service Bulletin
Airbus
Airbus
Airbus
Airbus
Revision
Mandatory Service Bulletin A300–53–6005 .....................................................................................
Mandatory Service Bulletin A310–53–2024 .....................................................................................
Mandatory Service Bulletin A310–53–2025 .....................................................................................
Service Bulletin A300–53–6006 .......................................................................................................
Date
04
05
06
3
July 18, 2007.
October 13, 2006.
August 3, 2006.
March 24, 1989.
Airbus Service Bulletin A300–53–6006,
Revision 3, dated March 24, 1989, contains
the following effective pages:
Revision level
shown on
page
Page Nos.
1, 29, 47, 48 ................................................................................................................................................
2–28, 30–46, 49–52 .....................................................................................................................................
CPrice-Sewell on DSKGBLS3C1PROD with RULES
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail: account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_
locations.html.
Issued in Renton, Washington, on
September 16, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–23094 Filed 9–28–09; 8:45 am]
BILLING CODE 4910–13–P
SUSQUEHANNA RIVER BASIN
COMMISSION
18 CFR Parts 806 and 808
Review and Approval of Projects
AGENCY: Susquehanna River Basin
Commission.
ACTION:
Final rule.
SUMMARY: This document contains
amendments to the project review
regulations of the Susquehanna River
Basin Commission (Commission)
including provisions restricting the use
of docket reopening petitions to avoid
abuses of process; amending the
‘‘Approval by Rule’’ (ABR) process to
allow for project sponsors to utilize
approved water sources at approved
drilling pad sites without the need for
modification of the ABR; clarifying that
the public hearing requirement for
rulemaking shall be applicable to the
proposed rulemaking stage of that
process; and further providing for the
time period within which
administrative appeals must be filed.
These amendments were first proposed
in a Notice of Proposed Rulemaking
(NOPR) that appeared at 74 FR 31647 on
July 2, 2009.
DATES: These rules are effective on
November 1, 2009.
VerDate Nov<24>2008
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2
Date shown on page
March 24, 1989.
August 11, 1988.
ADDRESSES: Susquehanna River Basin
Commission, 1721 N. Front Street,
Harrisburg, PA 17102–2391.
FOR FURTHER INFORMATION CONTACT:
Richard A. Cairo, General Counsel,
telephone: 717–238–0423, ext. 306; fax:
717–238–2436; e-mail: rcairo@srbc.net.
Also, for further information on the final
rulemaking, visit the Commission’s Web
site at https://www.srbc.net.
SUPPLEMENTARY INFORMATION:
Background and Purpose of
Amendments
The Commission convened public
hearings on August 4, 2009, in
Harrisburg, Pennsylvania and on August
5, 2009, in Elmira, New York. A written
comment period was held open until
August 15, 2009. Comments were
received at both the hearings and during
the comment period. A summary of the
comments and the Commission’s
responses thereto follows.
Comments by Section, Part 806
Section 806.4 Projects Requiring
Review and Approval
Comment: The Commission’s
proposal to require review and approval
for any hydroelectric project regulated
by the Federal Energy Regulatory
Commission (FERC) and initiating a
licensing or licensing amendment is
defective and should not be adopted
because: (1) As currently worded, the
E:\FR\FM\29SER1.SGM
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]]>Agencies
[Federal Register Volume 74, Number 187 (Tuesday, September 29, 2009)]
[Rules and Regulations]
[Pages 49805-49809]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-23094]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0431; Directorate Identifier 2007-NM-174-AD;
Amendment 39-16029; AD 2009-20-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-203 and -222
Airplanes and Model A300 B4-620 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This 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).
[[Page 49806]]
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. We are issuing this AD to require actions to correct the
unsafe condition on these products.
DATES: This AD becomes effective November 3, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 3,
2009.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on May 7, 2009 (74 FR
21274), and proposed to supersede AD 88-06-03, Amendment 39-5871 (53 FR
7730, March 10, 1988). That NPRM proposed 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 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 2007-0297 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, 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.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Request To Revise Paragraph (f)(4) of the NPRM
Airbus requests that we revise paragraph (f)(4) of the NPRM. Airbus
states that for the airplanes identified in paragraph (f)(4) of the
NPRM, it is not necessary to do the actions in accordance with the
service bulletins specified in paragraph (f)(4) of the NPRM. Airbus
further states that those airplanes are affected by Airworthiness
Limitation Item (ALI) Task 531919-01-1A, as specified in the service
bulletins identified in paragraph (f)(4) of this AD and the MCAI.
We agree with the commenter. The actions specified in paragraph
(f)(4) of the NPRM are not required for the airplanes identified in
that paragraph because those airplanes are already inspected in
accordance with ALI Task 531919-01-1A, and no additional actions are
necessary. We have confirmed with EASA that this is the intent of the
MCAI. We have removed paragraph (f)(4) of the NPRM as it is
unnecessary, and added a new Note 1 to this AD to clarify that no
action is required by this AD for the airplanes discussed in this
paragraph. We have re-identified the subsequent paragraphs accordingly.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 32 products of U.S.
registry. We also estimate that it will take about 668 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Required parts will 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
[[Page 49807]]
higher than estimated here. Based on these figures, we estimate the
cost of this AD to the 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
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 AD and placed it in the AD docket.
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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-5871 (53 FR
7730, March 10, 1988) and adding the following new AD:
2009-20-06 Airbus: Amendment 39-16029. Docket No. FAA-2009-0431;
Directorate Identifier 2007-NM-174-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
3, 2009.
Affected ADs
(b) This 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 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
Mandatory 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 Mandatory Service Bulletin
A300-53-6005, Revision 04, dated July 18, 2007; or Airbus Mandatory
Service Bulletin A310-53-2024, Revision 05, dated October 13, 2006;
as applicable.
[[Page 49808]]
(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.
Note 1: 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: No
action is required by this AD. For these airplanes, refer to Airbus
A300-600 ALI Task 531919-01-1A or Airbus A310 ALI Task 531919-01-1A,
as applicable, for guidance on the normal inspection program.
(4) 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.
----------------------------------------------------------------------------------------------------------------
(5) 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.
----------------------------------------------------------------------------------------------------------------
(6) 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 2: 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
------------------------------------------------------------------------
Airbus Mandatory Service 04 July 18, 2007.
Bulletin A300-53-6005.
Airbus Mandatory Service 05 October 13, 2006.
Bulletin A310-53-2024.
Airbus Mandatory Service 06 August 3, 2006.
Bulletin A310-53-2025.
[[Page 49809]]
Airbus Service Bulletin A300- 3 March 24, 1989.
53-6006.
------------------------------------------------------------------------
Material Incorporated by Reference
(i) You must use the service information contained in Table 4 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
Table 4--Material Incorporated by Reference
------------------------------------------------------------------------
Airbus Service Bulletin Revision Date
------------------------------------------------------------------------
Airbus Mandatory Service 04 July 18, 2007.
Bulletin A300-53-6005.
Airbus Mandatory Service 05 October 13, 2006.
Bulletin A310-53-2024.
Airbus Mandatory Service 06 August 3, 2006.
Bulletin A310-53-2025.
Airbus Service Bulletin A300- 3 March 24, 1989.
53-6006.
------------------------------------------------------------------------
Airbus Service Bulletin A300-53-6006, Revision 3, dated March
24, 1989, contains the following effective pages:
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Revision level
Page Nos. shown on page Date shown on page
------------------------------------------------------------------------
1, 29, 47, 48............... 3 March 24, 1989.
2-28, 30-46, 49-52.......... 2 August 11, 1988.
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(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on September 16, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-23094 Filed 9-28-09; 8:45 am]
BILLING CODE 4910-13-P
