Airworthiness Directives; Airbus Model A310 Series Airplanes, 29874-29879 [E7-10028]
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29874
Federal Register / Vol. 72, No. 103 / Wednesday, May 30, 2007 / Rules and Regulations
relative for issuance of an immigrant
visa under section 204(a) of the Act.
(When more than one petition is
submitted by the same petitioner on
behalf of orphans who are brothers or
sisters, only one fee will be required.)—
$670.
Form I–600A. For filing an
application for advance processing of
orphan petition. (When more than one
petition is submitted by the same
petitioner on behalf of orphans who are
brothers or sisters, only one fee will be
required.)—$670. No fee is charged if
Form I–600 has not yet been submitted
in connection with an approved Form I–
600A if a written request from the
applicant for an extension of the
approval has been received by USCIS
prior to the expiration date of approval
indicated on the Form I–171H. This
extension will require an update of the
applicant’s home study and a
determination from USCIS that proper
care will be provided to an adopted
orphan. A no fee extension is limited to
one occasion. If the Form I–600A
approval extension expires prior to
submission of an associated Form I–600,
then a complete application and fee
must be submitted for any subsequent
application.
Form I–601. For filing an application
for waiver of ground of inadmissibility
under section 212(h) or (i) of the Act.
(Only a single application and fee shall
be required when the alien is applying
simultaneously for a waiver under both
sections 212(h) and (i).)—$545.
Form I–612. For filing an application
for waiver of the foreign-residence
requirement under section 212(e) of the
Act—$545.
Form I–687. For filing an application
for status as a temporary resident under
section 245A(a) of the Act. A fee of $710
for each application is required at the
time of filing with the Department of
Homeland Security.
Form I–690. For filing an application
for waiver of a ground of inadmissibility
under section 212(a) of the Act as
amended, in conjunction with the
application under sections 210 or 245A
of the Act, or a petition under section
210A of the Act—$185.
Form I–694. For appealing the denial
of an applications under sections 210 or
245A of the Act, or a petition under
section 210A of the Act—$545.
Form I–695. For filing an application
for replacement of temporary resident
card (Form I–688)—$130.
Form I–698. For filing an application
for adjustment from temporary resident
status to that of lawful permanent
resident under section 245A(b)(1) of the
Act. For applicants filing within thirtyone months from the date of adjustment
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to temporary resident status, a fee of
$1,370 for each application is required
at the time of filing with the Department
of Homeland Security. For applicants
filing after thirty-one months from the
date of approval of temporary resident
status, who file their applications on or
after July 9, 1991, a fee of $1,410 is
required. The adjustment date is the
date of filing of the application for
permanent residence or the applicant’s
eligibility date, whichever is later.
*
*
*
*
*
Form I–751. For filing a petition to
remove the conditions on residence,
based on marriage—$465.
Form I–765. For filing an application
for employment authorization pursuant
to 8 CFR 274a.13—$340.
*
*
*
*
*
Form I–817. For filing an application
for voluntary departure under the
Family Unity Program—$440.
*
*
*
*
*
Form I–824. For filing for action on an
approved application or petition—$340.
Form I–829. For filing a petition by
entrepreneur to remove conditions—
$2,850.
*
*
*
*
*
Form N–300. For filing an application
for declaration of intention—$235.
Form N–336. For filing a request for
hearing on a decision in naturalization
proceedings under section 336 of the
Act—$605.
Form N–400. For filing an application
for naturalization (other than such
application filed on or after October 1,
2004, by an applicant who meets the
requirements of sections 328 or 329 of
the Act with respect to military service,
for which no fee is charged)—$595.
*
*
*
*
*
Form N–470. For filing an application
for benefits under section 316(b) or 317
of the Act—$305.
Form N–565. For filing an application
for a certificate of naturalization or
declaration of intention in lieu of a
certificate or declaration alleged to have
been lost, mutilated, or destroyed; for a
certificate of citizenship in a changed
name under section 343(c) of the Act; or
for a special certificate of naturalization
to obtain recognition as a citizen of the
United States by a foreign state under
section 343(b) of the Act—$380.
Form N–600. For filing an application
for a certificate of citizenship under
section 309(c) or section 341 of the
Act—$460, for applications filed on
behalf of a biological child and $420 for
applications filed on behalf of an
adopted child.
Form N–600K. For filing an
application for citizenship and issuance
of certificate under section 322 of the
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Act—$460, for an application filed on
behalf of a biological child and $420 for
an application filed on behalf of an
adopted child.
*
*
*
*
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(c) * * *
(5) No fee relating to any application,
petition, appeal, motion, or request
made to United States Citizenship and
Immigration Services may be waived
under paragraph (c)(1) of this section
except for the following: Biometrics;
Form I–90; Form I–485 (only in the case
of an alien in lawful nonimmigrant
status under sections 101(a)(15)(T) or
(U) of the Act; an applicant under
section 209(b) of the Act; an approved
self-petitioning battered or abused
spouse, parent, or child of a United
States citizen or lawful permanent
resident; or an alien to whom section
212(a)(4) of the Act does not apply with
respect to adjustment of status); Form I–
751; Form I–765; Form I–817; Form N–
300; Form N–336; Form N–400; Form
N–470; Form N–565; Form N–600; Form
N–600K; and Form I–290B and motions
filed with United States Citizenship and
Immigration Services relating to the
specified forms in this paragraph (c).
*
*
*
*
*
Dated: May 3, 2007.
Michael Chertoff,
Secretary.
[FR Doc. E7–10371 Filed 5–29–07; 8:45 am]
BILLING CODE 4410–10–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–26857; Directorate
Identifier 2006–NM–126–AD; Amendment
39–15069; AD 2007–11–12]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to all Airbus Model A310
series airplanes. That AD currently
requires inspections of the lower door
surrounding structure to detect cracks
and corrosion; inspections to detect
cracking of the holes of the corner
doublers, the fail-safe ring, and the door
frames of the door structures; and repair
if necessary. That AD also currently
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provides for optional terminating action
for certain inspections. This new AD
retains all requirements of the existing
AD, mandates the previously optional
terminating action, and reduces the
applicability of the existing AD. This
AD results from a determination that
further rulemaking is necessary to
improve the fatigue behavior of the
cabin door surroundings. We are issuing
this AD to prevent corrosion between
the scuff plates at exit and cargo doors
and fatigue cracks originating from
certain fastener holes located in
adjacent structure, which could result in
reduced structural integrity of the door
surroundings.
DATES: This AD becomes effective July
5, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of July 5, 2007.
On September 4, 1998 (63 FR 40819,
July 31, 1998), the Director of the
Federal Register approved the
incorporation by reference of certain
other publications listed in the AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 98–16–06, amendment
39–10682 (63 FR 40819, July 31, 1998).
The existing AD applies to all Airbus
Model A310 series airplanes. That
NPRM was published in the Federal
Register on January 19, 2007 (72 FR
2464). That NPRM proposed to retain
the requirements of AD 98–16–06.
These requirements are inspections of
the lower door surrounding structure to
detect cracks and corrosion; inspections
to detect cracking of the holes of the
corner doublers, the fail-safe ring, and
the door frames of the door structures;
and repair if necessary. That NPRM also
proposed to mandate the previously
optional terminating action, and reduce
the applicability of the existing AD.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Request To Give Credit for Previous
Inspections
FedEx concurs with the NPRM, but
requests that we give credit for previous
inspections (initial and repetitive)
accomplished in accordance with AD
98–16–06. FedEx points out that this
credit should be given for actions in
paragraphs (f), (g), and (l) of the NPRM.
We partially agree with the request.
We agree that it is necessary for the AD
to give credit for inspections
accomplished previously in accordance
with AD 98–16–06. We disagree that it
is necessary to change the AD in this
regard. Paragraph (e) of the AD states,
29875
‘‘You are responsible for having the
actions required by this AD performed
within the compliance times specified,
unless the actions have already been
done.’’ Therefore, the AD already gives
credit for required actions that were
accomplished according to AD 98–16–
06.
Explanation of New Service
Information
Airbus has issued Service Bulletin
A310–53–2037, Revision 03, including
Appendix 01, dated July 26, 2006. We
referred in the NPRM to Service Bulletin
A310–53–2037, Revision 1, dated April
29, 1992; and Revision 02, dated
November 27, 2000; as the appropriate
source of service information for
accomplishing certain actions. Revision
03 of the service bulletin updates the
effectivity and improves the inspection
and repair procedures. Revision 03
states that no additional work is
required for airplanes modified in
accordance with Revision 02 or any
previous revision. We have changed
Table 1 in paragraph (n) of this AD to
refer to Revision 03 for accomplishing
certain required actions, and we have
changed Table 3 in paragraph (p) of this
AD to give credit to operators who
accomplished the actions in accordance
with Revision 02 of the service bulletin.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. We have
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD. The average labor
rate per work hour is $80.
ESTIMATED COSTS
Number of
U.S.registered
airplanes
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Action
Work hours
Parts
Cost per airplane
Repetitive inspections
behind scuff plates
(required by AD 98–
16–06).
Repetitive inspections of
corner doublers, failsafe ring, and door
frames (required by
AD 98–16–06).
26 .................................
None .............................
$2,080 ..........................
46
$95,680.
Between 4 and 100 depending on kit purchased.
None .............................
Between $320 and
$8,000.
46
Between $14,720, and
$368,000 per inspection cycle.
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Fleet cost
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Federal Register / Vol. 72, No. 103 / Wednesday, May 30, 2007 / Rules and Regulations
ESTIMATED COSTS—Continued
Action
Terminating modification
for repetitive inspection of corner doublers, fail-safe ring,
and door frames.
Work hours
Between 8 and 55 depending on kit purchased.
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.
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Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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Cost per airplane
Between $506 and
$6,098 depending on
kit purchased.
Between $1,146 and
$10,498.
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–10682 (63
FR 40819, July 31, 1998) and by adding
the following new airworthiness
directive (AD):
I
2007–11–12 Airbus: Amendment 39–15069.
Docket No. FAA–2007–26857;
Directorate Identifier 2006–NM–126–AD.
Effective Date
(a) This AD becomes effective July 5, 2007.
Affected ADs
(b) This AD supersedes AD 98–16–06.
Applicability
(c) This AD applies to Airbus Model A310
series airplanes; certificated in any category;
excluding those airplanes on which Airbus
Modifications 5068, 7201, and 7298 have
been incorporated in production.
Unsafe Condition
(d) This AD results from a determination
that further rulemaking is necessary to
improve the fatigue behavior of the cabin
door surroundings. We are issuing this AD to
prevent corrosion between the scuff plates at
exit and cargo doors and fatigue cracks
originating from certain fastener holes
located in adjacent structure, which could
result in reduced structural integrity of the
door surroundings.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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Number of
U.S.registered
airplanes
Sfmt 4700
46
Fleet cost
Between $52,716 and
$482,908.
Requirements of AD 98–16–06
Initial Inspection Behind Scuff Plates and
Repair if Necessary With Revised Affected
Doors
(f) Perform an initial inspection of the areas
behind the scuff plates below the passenger/
crew doors and bulk cargo door to detect
cracks and corrosion, in accordance with
Airbus Service Bulletin A310–53–2030,
Revision 5, dated March 6, 1991, at the
applicable time specified in paragraph (f)(1),
(f)(2), or (f)(3) of this AD. If any crack or
corrosion is found during this inspection,
prior to further flight, repair in accordance
with the service bulletin. Accomplishment of
this inspection is not required for the aft
passenger/crew doors if a steel doubler that
covers the entire inspection area is installed.
(1) For any door on which Modification
5382 and Modification 5382D4741 for all
other doors have been accomplished: Perform
the initial inspection within 9 years since
airplane manufacture, or within 1 year after
September 4, 1998 (the effective date of AD
98–16–06), whichever occurs later.
(2) For any door on which Modification
5382 and Modification 5382D4741 for all
other doors have not been accomplished, and
on which the procedures described in Airbus
Service Bulletin A310–53–2004, Revision 2,
dated June 17, 1985; or Airbus Service
Information Letter 53–033, Revision 2, dated
November 23, 1984; have been accomplished:
Perform the initial inspection within 5 years
since airplane manufacture, or within 1 year
after September 4, 1998, whichever occurs
later.
(3) For any door on which Modification
5382 and Modification 5382D4741 for all
other doors have not been accomplished, and
on which the procedures described in Airbus
Service Bulletin A310–53–2004, Revision 2,
dated June 17, 1985; or Airbus Service
Information Letter 53–033, Revision 2, dated
November 23, 1984; have not been
accomplished: Perform the initial inspection
within 4 years since airplane manufacture, or
within 1 year after September 4, 1998,
whichever occurs later.
Repetitive Inspections Behind Scuff Plates
(g) Perform repetitive inspections of the
areas behind the scuff plates below the
passenger/crew doors and bulk cargo door to
detect cracks and corrosion, in accordance
with Airbus Service Bulletin A310–53–2041,
Revision 02, dated July 2, 1996, at the
applicable times specified in paragraphs
(g)(1), (g)(2), and (g)(3) of this AD.
Accomplishment of these inspections is not
required for the aft passenger/crew doors if
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a steel doubler that covers the entire
inspection area is installed.
(1) For the forward passenger/crew doors,
the bulk cargo door, and the aft passenger/
crew doors, except the upper and lower
edges of the fail-safe ring and the upper edges
of the corner doubler, on all Model A310–200
and –300 series airplanes: Perform the first
inspection within 5 years after accomplishing
the inspection required by paragraph (f) of
this AD; and repeat the inspection thereafter
at intervals not to exceed 5 years.
(2) For the upper and lower edges of the
fail-safe ring and the upper edges of the
corner doubler of the aft passenger/crew door
on all Model A310–200 series airplanes:
Perform the first inspection within 5 years or
12,000 landings after accomplishing the
inspection required by paragraph (f) of this
AD, whichever occurs first; and repeat the
inspection thereafter at intervals not to
exceed 5 years or 12,000 landings, whichever
occurs first.
(3) For the upper and lower edges of the
fail-safe ring and the upper edges of the
corner doubler of the aft passenger/crew door
on all Model A310–300 series airplanes:
Perform the first inspection within 5 years or
7,000 landings after accomplishing the
inspection required by paragraph (f) of this
AD, whichever occurs first; and repeat the
inspection thereafter at intervals not to
exceed 5 years or 7,000 landings, whichever
occurs first.
Repair of Scuff Plates if Necessary
(h) If any crack is found during any
inspection required by paragraph (g) or (n) of
this AD, prior to further flight, repair in
accordance with Airbus Service Bulletin
A310–53–2041, Revision 02, dated July 2,
1996. Thereafter, perform the repetitive
inspections required by paragraph (g) of this
AD at the applicable times specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
(i) If any corrosion is found during any
inspection required by paragraph (g) of this
AD, prior to further flight, repair in
accordance with Airbus Service Bulletin
A310–53–2041, Revision 02, dated July 2,
1996. Thereafter, perform the repetitive
inspections required by paragraph (g) of this
AD at the applicable time specified in
paragraph (i)(1) or (i)(2) of this AD.
(1) For Model A310–200 series airplanes:
Inspect at intervals not to exceed 5 years or
9,600 landings, whichever occurs first.
(2) For Model A310–300 series airplanes:
Inspect at intervals not to exceed 5 years or
5,600 landings, whichever occurs first.
(j) Accomplishment of the actions required
by paragraph (g), (h), or (i) of this AD in
accordance with Airbus Service Bulletin
A310–53–2041, dated December 5, 1990; or
Revision 01, dated March 6, 1991; prior to
September 4, 1998, is acceptable for
compliance with that paragraph.
Initial Inspection of Corner Doublers, FailSafe Ring, and Door Frames
(k) Perform an inspection to detect
cracking of the holes of the corner doublers,
the fail-safe ring, and the door frames of the
left- and right-hand forward, mid, and aft
passenger/crew door structures, in
accordance with Airbus Service Bulletin
A310–53–2037, Revision 1, dated April 29,
1992, and at the applicable times specified in
paragraphs (k)(1), (k)(2), and (k)(3) of this AD.
(1) For the upper corners of the forward
doors: Inspect prior to the accumulation of
20,000 total landings, or within 2,000
landings after September 4, 1998, whichever
occurs later.
(2) For the lower corners of the forward
doors: Inspect prior to the accumulation of
20,000 total landings, or within 4,000
landings after September 4, 1998, whichever
occurs later.
(3) For the upper and lower corners of the
aft doors, and for the parts underneath the
corners of the upper door frames: Inspect
prior to the accumulation of 20,000 total
landings, or within 4,000 landings after
September 4, 1998, whichever occurs later.
Repetitive Inspections of Corner Doublers,
Fail-Safe Ring, and Door Frames
(l) Repeat the inspections required by
paragraph (k) of this AD at the applicable
times specified in paragraphs (l)(1), (l)(2),
(l)(3), (l)(4), and (l)(5).
(1) For the upper corners of the forward
doors: Inspect at intervals not to exceed 6,000
landings.
29877
(2) For the lower corners of the forward
doors: Inspect at intervals not to exceed
10,000 landings.
(3) For the upper and lower corners of the
aft doors on which an inspection required by
paragraph (k) of this AD was accomplished
using a ROTO test technique: Inspect at
intervals not to exceed 8,000 landings.
(4) For the upper and lower corners of the
aft doors on which an inspection required by
paragraph (k) of this AD was accomplished
using an x-ray technique: Inspect at intervals
not to exceed 3,500 landings.
(5) For the areas around the fasteners in the
vicinity of stringer 12 on the upper door
frames of the aft doors on which an
inspection required by paragraph (k) of this
AD was accomplished using a visual
technique: Inspect at intervals not to exceed
6,900 landings.
Repair of Corner Doublers, Fail-Safe Ring,
and/or Door Frames if Necessary
(m) If any crack is found during any
inspection required by paragraph (k) or (l) of
this AD: Prior to further flight, accomplish
the requirement of paragraph (m)(1) or (m)(2)
of this AD, as applicable.
(1) If any crack is found, and the crack can
be eliminated using the method specified in
Airbus Service Bulletin A310–53–2037,
Revision 1, dated April 29, 1992; or Revision
02, dated November 27, 2000: Prior to further
flight, repair the crack in accordance with
that service bulletin.
(2) If any crack is found, and the crack
cannot be eliminated using the method
specified in Airbus Service Bulletin A310–
53–2037, Revision 1, dated April 29, 1992; or
Revision 02, dated November 27, 2000: Prior
to further flight, repair the crack in
accordance with a method approved by the
Manager, International Branch, ANM–116,
FAA, Transport Airplane Directorate.
New Requirements of This AD
New Revision of Service Bulletins
(n) As of the effective date of this AD, use
only the service bulletins specified in Table
1 of this AD.
TABLE 1.—NEW REVISION OF SERVICE BULLETINS
Do the action(s) required by—
In accordance with the accomplishment instructions of Airbus Service
Bulletin—
(1) Paragraph (f) of this AD ......................................................................
(2) Paragraph (k) and (m)(1) of this AD ...................................................
A310–53–2030, Revision 06, dated July 2, 1996.
A310–53–2037, Revision 03, excluding Appendix 01, dated July 26,
2006.
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Terminating Modification for Repetitive
Inspection of Corner Doublers, Fail-Safe
Ring, and Door Frames
(o) Modify the passenger/crew door
structures in accordance with the
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Accomplishment Instructions of Airbus
Service Bulletin A310–53–2017, Revision 09,
dated May 17, 2004. Do the modification at
the applicable time in paragraph (o)(1) or
(o)(2) of Table 2 of this AD. Accomplishment
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of this modification constitutes terminating
action for the repetitive inspections required
by paragraph (l) of this AD. The inspections
required by paragraph (f) of this AD must be
done before accomplishing this modification.
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TABLE 2.—COMPLIANCE TIME FOR TERMINATING MODIFICATION
For model—
Compliance time
(1) A310–203, –204, –221, and –222 airplanes ......................................
Before the accumulation of 40,000 flight cycles since the date of
issuance of the original French standard Airworthiness Certificate or
the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of
this AD, whichever occurs later.
Before the accumulation of 35,000 flight cycles since the date of
issuance of the original French standard Airworthiness Certificate or
the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of
this AD, whichever occurs later.
(2) A310–304, –322, –324, and –325 airplanes ......................................
Earlier Revision of Service Bulletins
(p) Actions done before the effective date
of this AD in accordance with the service
bulletins identified in Table 3 of this AD are
acceptable for compliance with the
corresponding requirements of this AD.
TABLE 3.—EARLIER REVISION(S) OF SERVICE BULLETINS
Revision
level
Airbus Service Bulletin
(1) A310–53–2017 ...........................................................................................................................................
(2) A310–53–2017 ...........................................................................................................................................
(3) A310–53–2037 ...........................................................................................................................................
Alternative Methods of Compliance
(AMOCs)
(q)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Alternative methods of compliance,
approved previously in accordance with AD
98–16–06 are approved as alternative
methods of compliance with the
corresponding provisions of paragraphs (f)
through (m) of this AD.
(3) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
07
08
02
Date
February 25, 1992.
September 7, 2000.
November 27, 2000.
Related Information
(r) French airworthiness directives 1991–
132–124(B) R1, dated November 29, 2000,
and F–2004–103, dated July 7, 2004, also
address the subject of this AD.
Material Incorporated by Reference
(s) You must use the service information
listed in Table 4 of this AD to perform the
actions that are required by this AD, unless
the AD specifies otherwise.
TABLE 4.—ALL MATERIAL INCORPORATED BY REFERENCE
Revision
level
Airbus Service Bulletin
A310–53–2017 .................................................................................................................................................
A310–53–2030 .................................................................................................................................................
A310–53–2030 .................................................................................................................................................
A310–53–2037 .................................................................................................................................................
A310–53–2037, excluding Appendix 01 ..........................................................................................................
A310–53–2037, excluding Appendix 01 ..........................................................................................................
A310–53–2041 .................................................................................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the documents listed in Table 5 of this AD
09
5
06
1
02
03
02
Date
May 17, 2004.
March 6, 1991.
July 2, 1996.
April 29, 1992.
November 27, 2000.
July 26, 2006.
July 2, 1996.
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 5.—NEW MATERIAL INCORPORATED BY REFERENCE
Revision
level
cprice-sewell on PRODPC61 with RULES
Airbus Service Bulletin
A310–53–2017 .................................................................................................................................................
A310–53–2030 .................................................................................................................................................
A310–53–2037 .................................................................................................................................................
A310–53–2037, excluding Appendix 01 ..........................................................................................................
A310–53–2037, excluding Appendix 01 ..........................................................................................................
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E:\FR\FM\30MYR1.SGM
09
06
1
02
03
30MYR1
Date
May 17, 2004.
July 2, 1996.
April 29, 1992.
November 27, 2000.
July 26, 2006.
Federal Register / Vol. 72, No. 103 / Wednesday, May 30, 2007 / Rules and Regulations
29879
Airbus Service Bulletin A310–53–2037,
Revision 1, dated April 29, 1992, contains the
following effective pages:
Page No.
Revision level shown on page
1, 4, 6, 11–15, 18, 29, 39–44, 46, 57 ...................................
2, 3, 5, 7–10, 16, 17, 19–28, 30–38, 45,47–56, 58–60 .......
Revision 1 ............................................................................
Original .................................................................................
(2) On September 4, 1998 (63 FR 40819,
July 31, 1998), the Director of the Federal
Register approved the incorporation by
Date shown on page
April 29, 1992.
December 11, 1990.
reference of the service information listed in
Table 6 of this AD.
TABLE 6.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Revision
level
Airbus Service Bulletin
A310–53–2030 ..........................................................................................................................................................
A310–53–2041 ..........................................................................................................................................................
(3) Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or 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/
cfr/ibr-locations.html.
Issued in Renton, Washington, on May 15,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10028 Filed 5–29–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27494; Directorate
Identifier 2006–NM–269–AD; Amendment
39–15071; AD 2007–11–14]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135BJ
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
cprice-sewell on PRODPC61 with RULES
VerDate Aug<31>2005
15:13 May 29, 2007
Jkt 211001
It has been found that both fuel level
control units (LCU) and their associated
harnesses throughout the aircraft does not
comply with the requirements of proper
segregation, in order to preclude a possible
ignition source in the vicinity of the fuel
tanks, as required by SFAR (Special Federal
Aviation Regulation) 88 regulations.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective July
5, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 5, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington.
Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
Streamlined Issuance of AD
We are adopting a new
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
SUMMARY:
product. The MCAI describes the unsafe
condition as:
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
PO 00000
Frm 00043
Fmt 4700
Sfmt 4700
5
02
Date
March 6, 1991.
July 2, 1996.
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
MCAI and for this reason might not
follow our plain language principles.
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 March 8, 2007 (72 FR
10429). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
It has been found that both fuel level
control units (LCU) and their associated
harnesses throughout the aircraft does not
comply with the requirements of proper
segregation, in order to preclude a possible
ignition source in the vicinity of the fuel
tanks, as required by SFAR (Special Federal
Aviation Regulation) 88 regulations.
The MCAI requires replacing the fuel
LCU 1 and LCU 2; reworking the LCU
1 and LCU 2 supports; and segregating,
replacing, and reworking some
harnesses.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
E:\FR\FM\30MYR1.SGM
30MYR1
]]>Agencies
[Federal Register Volume 72, Number 103 (Wednesday, May 30, 2007)]
[Rules and Regulations]
[Pages 29874-29879]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10028]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-26857; Directorate Identifier 2006-NM-126-AD;
Amendment 39-15069; AD 2007-11-12]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to all Airbus Model A310 series airplanes. That AD
currently requires inspections of the lower door surrounding structure
to detect cracks and corrosion; inspections to detect cracking of the
holes of the corner doublers, the fail-safe ring, and the door frames
of the door structures; and repair if necessary. That AD also currently
[[Page 29875]]
provides for optional terminating action for certain inspections. This
new AD retains all requirements of the existing AD, mandates the
previously optional terminating action, and reduces the applicability
of the existing AD. This AD results from a determination that further
rulemaking is necessary to improve the fatigue behavior of the cabin
door surroundings. We are issuing this AD to prevent corrosion between
the scuff plates at exit and cargo doors and fatigue cracks originating
from certain fastener holes located in adjacent structure, which could
result in reduced structural integrity of the door surroundings.
DATES: This AD becomes effective July 5, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of July 5, 2007.
On September 4, 1998 (63 FR 40819, July 31, 1998), the Director of
the Federal Register approved the incorporation by reference of certain
other publications listed in the AD.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 98-16-06, amendment 39-
10682 (63 FR 40819, July 31, 1998). The existing AD applies to all
Airbus Model A310 series airplanes. That NPRM was published in the
Federal Register on January 19, 2007 (72 FR 2464). That NPRM proposed
to retain the requirements of AD 98-16-06. These requirements are
inspections of the lower door surrounding structure to detect cracks
and corrosion; inspections to detect cracking of the holes of the
corner doublers, the fail-safe ring, and the door frames of the door
structures; and repair if necessary. That NPRM also proposed to mandate
the previously optional terminating action, and reduce the
applicability of the existing AD.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Give Credit for Previous Inspections
FedEx concurs with the NPRM, but requests that we give credit for
previous inspections (initial and repetitive) accomplished in
accordance with AD 98-16-06. FedEx points out that this credit should
be given for actions in paragraphs (f), (g), and (l) of the NPRM.
We partially agree with the request. We agree that it is necessary
for the AD to give credit for inspections accomplished previously in
accordance with AD 98-16-06. We disagree that it is necessary to change
the AD in this regard. Paragraph (e) of the AD states, ``You are
responsible for having the actions required by this AD performed within
the compliance times specified, unless the actions have already been
done.'' Therefore, the AD already gives credit for required actions
that were accomplished according to AD 98-16-06.
Explanation of New Service Information
Airbus has issued Service Bulletin A310-53-2037, Revision 03,
including Appendix 01, dated July 26, 2006. We referred in the NPRM to
Service Bulletin A310-53-2037, Revision 1, dated April 29, 1992; and
Revision 02, dated November 27, 2000; as the appropriate source of
service information for accomplishing certain actions. Revision 03 of
the service bulletin updates the effectivity and improves the
inspection and repair procedures. Revision 03 states that no additional
work is required for airplanes modified in accordance with Revision 02
or any previous revision. We have changed Table 1 in paragraph (n) of
this AD to refer to Revision 03 for accomplishing certain required
actions, and we have changed Table 3 in paragraph (p) of this AD to
give credit to operators who accomplished the actions in accordance
with Revision 02 of the service bulletin.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this AD. The average labor rate per work hour is $80.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Cost per U.S.-
Action Work hours Parts airplane registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
Repetitive inspections behind 26.............. None............ $2,080......... 46 $95,680.
scuff plates (required by AD
98-16-06).
Repetitive inspections of Between 4 and None............ Between $320 46 Between
corner doublers, fail-safe 100 depending and $8,000. $14,720, and
ring, and door frames on kit $368,000 per
(required by AD 98-16-06). purchased. inspection
cycle.
[[Page 29876]]
Terminating modification for Between 8 and 55 Between $506 and Between $1,146 46 Between $52,716
repetitive inspection of depending on $6,098 and $10,498. and $482,908.
corner doublers, fail-safe kit purchased. depending on
ring, and door frames. kit purchased.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-10682 (63 FR 40819, July 31, 1998) and by adding
the following new airworthiness directive (AD):
2007-11-12 Airbus: Amendment 39-15069. Docket No. FAA-2007-26857;
Directorate Identifier 2006-NM-126-AD.
Effective Date
(a) This AD becomes effective July 5, 2007.
Affected ADs
(b) This AD supersedes AD 98-16-06.
Applicability
(c) This AD applies to Airbus Model A310 series airplanes;
certificated in any category; excluding those airplanes on which
Airbus Modifications 5068, 7201, and 7298 have been incorporated in
production.
Unsafe Condition
(d) This AD results from a determination that further rulemaking
is necessary to improve the fatigue behavior of the cabin door
surroundings. We are issuing this AD to prevent corrosion between
the scuff plates at exit and cargo doors and fatigue cracks
originating from certain fastener holes located in adjacent
structure, which could result in reduced structural integrity of the
door surroundings.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Requirements of AD 98-16-06
Initial Inspection Behind Scuff Plates and Repair if Necessary With
Revised Affected Doors
(f) Perform an initial inspection of the areas behind the scuff
plates below the passenger/crew doors and bulk cargo door to detect
cracks and corrosion, in accordance with Airbus Service Bulletin
A310-53-2030, Revision 5, dated March 6, 1991, at the applicable
time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD. If
any crack or corrosion is found during this inspection, prior to
further flight, repair in accordance with the service bulletin.
Accomplishment of this inspection is not required for the aft
passenger/crew doors if a steel doubler that covers the entire
inspection area is installed.
(1) For any door on which Modification 5382 and Modification
5382D4741 for all other doors have been accomplished: Perform the
initial inspection within 9 years since airplane manufacture, or
within 1 year after September 4, 1998 (the effective date of AD 98-
16-06), whichever occurs later.
(2) For any door on which Modification 5382 and Modification
5382D4741 for all other doors have not been accomplished, and on
which the procedures described in Airbus Service Bulletin A310-53-
2004, Revision 2, dated June 17, 1985; or Airbus Service Information
Letter 53-033, Revision 2, dated November 23, 1984; have been
accomplished: Perform the initial inspection within 5 years since
airplane manufacture, or within 1 year after September 4, 1998,
whichever occurs later.
(3) For any door on which Modification 5382 and Modification
5382D4741 for all other doors have not been accomplished, and on
which the procedures described in Airbus Service Bulletin A310-53-
2004, Revision 2, dated June 17, 1985; or Airbus Service Information
Letter 53-033, Revision 2, dated November 23, 1984; have not been
accomplished: Perform the initial inspection within 4 years since
airplane manufacture, or within 1 year after September 4, 1998,
whichever occurs later.
Repetitive Inspections Behind Scuff Plates
(g) Perform repetitive inspections of the areas behind the scuff
plates below the passenger/crew doors and bulk cargo door to detect
cracks and corrosion, in accordance with Airbus Service Bulletin
A310-53-2041, Revision 02, dated July 2, 1996, at the applicable
times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
Accomplishment of these inspections is not required for the aft
passenger/crew doors if
[[Page 29877]]
a steel doubler that covers the entire inspection area is installed.
(1) For the forward passenger/crew doors, the bulk cargo door,
and the aft passenger/crew doors, except the upper and lower edges
of the fail-safe ring and the upper edges of the corner doubler, on
all Model A310-200 and -300 series airplanes: Perform the first
inspection within 5 years after accomplishing the inspection
required by paragraph (f) of this AD; and repeat the inspection
thereafter at intervals not to exceed 5 years.
(2) For the upper and lower edges of the fail-safe ring and the
upper edges of the corner doubler of the aft passenger/crew door on
all Model A310-200 series airplanes: Perform the first inspection
within 5 years or 12,000 landings after accomplishing the inspection
required by paragraph (f) of this AD, whichever occurs first; and
repeat the inspection thereafter at intervals not to exceed 5 years
or 12,000 landings, whichever occurs first.
(3) For the upper and lower edges of the fail-safe ring and the
upper edges of the corner doubler of the aft passenger/crew door on
all Model A310-300 series airplanes: Perform the first inspection
within 5 years or 7,000 landings after accomplishing the inspection
required by paragraph (f) of this AD, whichever occurs first; and
repeat the inspection thereafter at intervals not to exceed 5 years
or 7,000 landings, whichever occurs first.
Repair of Scuff Plates if Necessary
(h) If any crack is found during any inspection required by
paragraph (g) or (n) of this AD, prior to further flight, repair in
accordance with Airbus Service Bulletin A310-53-2041, Revision 02,
dated July 2, 1996. Thereafter, perform the repetitive inspections
required by paragraph (g) of this AD at the applicable times
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
(i) If any corrosion is found during any inspection required by
paragraph (g) of this AD, prior to further flight, repair in
accordance with Airbus Service Bulletin A310-53-2041, Revision 02,
dated July 2, 1996. Thereafter, perform the repetitive inspections
required by paragraph (g) of this AD at the applicable time
specified in paragraph (i)(1) or (i)(2) of this AD.
(1) For Model A310-200 series airplanes: Inspect at intervals
not to exceed 5 years or 9,600 landings, whichever occurs first.
(2) For Model A310-300 series airplanes: Inspect at intervals
not to exceed 5 years or 5,600 landings, whichever occurs first.
(j) Accomplishment of the actions required by paragraph (g),
(h), or (i) of this AD in accordance with Airbus Service Bulletin
A310-53-2041, dated December 5, 1990; or Revision 01, dated March 6,
1991; prior to September 4, 1998, is acceptable for compliance with
that paragraph.
Initial Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames
(k) Perform an inspection to detect cracking of the holes of the
corner doublers, the fail-safe ring, and the door frames of the
left- and right-hand forward, mid, and aft passenger/crew door
structures, in accordance with Airbus Service Bulletin A310-53-2037,
Revision 1, dated April 29, 1992, and at the applicable times
specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD.
(1) For the upper corners of the forward doors: Inspect prior to
the accumulation of 20,000 total landings, or within 2,000 landings
after September 4, 1998, whichever occurs later.
(2) For the lower corners of the forward doors: Inspect prior to
the accumulation of 20,000 total landings, or within 4,000 landings
after September 4, 1998, whichever occurs later.
(3) For the upper and lower corners of the aft doors, and for
the parts underneath the corners of the upper door frames: Inspect
prior to the accumulation of 20,000 total landings, or within 4,000
landings after September 4, 1998, whichever occurs later.
Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door
Frames
(l) Repeat the inspections required by paragraph (k) of this AD
at the applicable times specified in paragraphs (l)(1), (l)(2),
(l)(3), (l)(4), and (l)(5).
(1) For the upper corners of the forward doors: Inspect at
intervals not to exceed 6,000 landings.
(2) For the lower corners of the forward doors: Inspect at
intervals not to exceed 10,000 landings.
(3) For the upper and lower corners of the aft doors on which an
inspection required by paragraph (k) of this AD was accomplished
using a ROTO test technique: Inspect at intervals not to exceed
8,000 landings.
(4) For the upper and lower corners of the aft doors on which an
inspection required by paragraph (k) of this AD was accomplished
using an x-ray technique: Inspect at intervals not to exceed 3,500
landings.
(5) For the areas around the fasteners in the vicinity of
stringer 12 on the upper door frames of the aft doors on which an
inspection required by paragraph (k) of this AD was accomplished
using a visual technique: Inspect at intervals not to exceed 6,900
landings.
Repair of Corner Doublers, Fail-Safe Ring, and/or Door Frames if
Necessary
(m) If any crack is found during any inspection required by
paragraph (k) or (l) of this AD: Prior to further flight, accomplish
the requirement of paragraph (m)(1) or (m)(2) of this AD, as
applicable.
(1) If any crack is found, and the crack can be eliminated using
the method specified in Airbus Service Bulletin A310-53-2037,
Revision 1, dated April 29, 1992; or Revision 02, dated November 27,
2000: Prior to further flight, repair the crack in accordance with
that service bulletin.
(2) If any crack is found, and the crack cannot be eliminated
using the method specified in Airbus Service Bulletin A310-53-2037,
Revision 1, dated April 29, 1992; or Revision 02, dated November 27,
2000: Prior to further flight, repair the crack in accordance with a
method approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate.
New Requirements of This AD
New Revision of Service Bulletins
(n) As of the effective date of this AD, use only the service
bulletins specified in Table 1 of this AD.
Table 1.--New Revision of Service Bulletins
------------------------------------------------------------------------
In accordance with the
Do the action(s) required by-- accomplishment instructions of
Airbus Service Bulletin--
------------------------------------------------------------------------
(1) Paragraph (f) of this AD........... A310-53-2030, Revision 06,
dated July 2, 1996.
(2) Paragraph (k) and (m)(1) of this AD A310-53-2037, Revision 03,
excluding Appendix 01, dated
July 26, 2006.
------------------------------------------------------------------------
Terminating Modification for Repetitive Inspection of Corner Doublers,
Fail-Safe Ring, and Door Frames
(o) Modify the passenger/crew door structures in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A310-53-
2017, Revision 09, dated May 17, 2004. Do the modification at the
applicable time in paragraph (o)(1) or (o)(2) of Table 2 of this AD.
Accomplishment of this modification constitutes terminating action
for the repetitive inspections required by paragraph (l) of this AD.
The inspections required by paragraph (f) of this AD must be done
before accomplishing this modification.
[[Page 29878]]
Table 2.--Compliance Time for Terminating Modification
------------------------------------------------------------------------
For model-- Compliance time
------------------------------------------------------------------------
(1) A310-203, -204, -221, and -222 Before the accumulation of
airplanes. 40,000 flight cycles since the
date of issuance of the
original French standard
Airworthiness Certificate or
the date of issuance of the
original French Export
Certificate of Airworthiness,
or during the next inspection
required by paragraph (l) of
this AD, whichever occurs
later.
(2) A310-304, -322, -324, and -325 Before the accumulation of
airplanes. 35,000 flight cycles since the
date of issuance of the
original French standard
Airworthiness Certificate or
the date of issuance of the
original French Export
Certificate of Airworthiness,
or during the next inspection
required by paragraph (l) of
this AD, whichever occurs
later.
------------------------------------------------------------------------
Earlier Revision of Service Bulletins
(p) Actions done before the effective date of this AD in
accordance with the service bulletins identified in Table 3 of this
AD are acceptable for compliance with the corresponding requirements
of this AD.
Table 3.--Earlier Revision(s) of Service Bulletins
------------------------------------------------------------------------
Revision
Airbus Service Bulletin level Date
------------------------------------------------------------------------
(1) A310-53-2017.............. 07 February 25, 1992.
(2) A310-53-2017.............. 08 September 7, 2000.
(3) A310-53-2037.............. 02 November 27, 2000.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(q)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Alternative methods of compliance, approved previously in
accordance with AD 98-16-06 are approved as alternative methods of
compliance with the corresponding provisions of paragraphs (f)
through (m) of this AD.
(3) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(r) French airworthiness directives 1991-132-124(B) R1, dated
November 29, 2000, and F-2004-103, dated July 7, 2004, also address
the subject of this AD.
Material Incorporated by Reference
(s) You must use the service information listed in Table 4 of
this AD to perform the actions that are required by this AD, unless
the AD specifies otherwise.
Table 4.--All Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Airbus Service Bulletin level Date
------------------------------------------------------------------------
A310-53-2017.................. 09 May 17, 2004.
A310-53-2030.................. 5 March 6, 1991.
A310-53-2030.................. 06 July 2, 1996.
A310-53-2037.................. 1 April 29, 1992.
A310-53-2037, excluding 02 November 27, 2000.
Appendix 01.
A310-53-2037, excluding 03 July 26, 2006.
Appendix 01.
A310-53-2041.................. 02 July 2, 1996.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the documents listed in Table 5 of
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Table 5.--New Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Airbus Service Bulletin level Date
------------------------------------------------------------------------
A310-53-2017.................. 09 May 17, 2004.
A310-53-2030.................. 06 July 2, 1996.
A310-53-2037.................. 1 April 29, 1992.
A310-53-2037, excluding 02 November 27, 2000.
Appendix 01.
A310-53-2037, excluding 03 July 26, 2006.
Appendix 01.
------------------------------------------------------------------------
[[Page 29879]]
Airbus Service Bulletin A310-53-2037, Revision 1, dated April
29, 1992, contains the following effective pages:
----------------------------------------------------------------------------------------------------------------
Page No. Revision level shown on page Date shown on page
----------------------------------------------------------------------------------------------------------------
1, 4, 6, 11-15, 18, 29, 39-44, 46, 57.... Revision 1.................. April 29, 1992.
2, 3, 5, 7-10, 16, 17, 19-28, 30-38, Original.................... December 11, 1990.
45,47-56, 58-60.
----------------------------------------------------------------------------------------------------------------
(2) On September 4, 1998 (63 FR 40819, July 31, 1998), the
Director of the Federal Register approved the incorporation by
reference of the service information listed in Table 6 of this AD.
Table 6.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
Revision
Airbus Service Bulletin level Date
------------------------------------------------------------------------
A310-53-2030..................... 5 March 6, 1991.
A310-53-2041..................... 02 July 2, 1996.
------------------------------------------------------------------------
(3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service information. You may
review copies at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on May 15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-10028 Filed 5-29-07; 8:45 am]
BILLING CODE 4910-13-P
