Airworthiness Directives; Airbus Model A318, A319, A320 and A321 Airplanes, 12077-12080 [E7-4535]
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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations
(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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains the
NPRM, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5227) 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
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 FAA amends § 39.13 by adding
the following new AD:
I
2007–06–04 EADS SOCATA: Amendment
39–14985; Docket No. FAA–2006–26231;
Directorate Identifier 2006–CE–61–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 19, 2007.
Affected ADs
(b) None.
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Applicability
(c) This AD applies to Model TBM 700
airplanes, serial numbers 1 through 268, and
270 through 327, certificated in any category.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states
reports of two fatigue failures of flap carriage
rollpins that occurred on in-service airplanes.
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14:08 Mar 14, 2007
Jkt 211001
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) Within the next 100 hours time-inservice (TIS) after April 19, 2007 (the
effective date of this AD), inspect all flap
inboard carriage rollpins for proper torque
values and correct as necessary before further
flight.
(2) Repeat these inspections thereafter at
intervals not to exceed 100 hours TIS and
correct as necessary before further flight after
the inspection in which a correction is
necessary.
(3) Accomplish these actions according to
the instructions given in EADS SOCATA
TBM Aircraft Mandatory Service Bulletin SB
70–122, Amendment 1, dated March 2006, or
EADS SOCATA TBM Aircraft Mandatory
Service Bulletin SB 70–122, Amendment 2,
dated January 2007, and the applicable
maintenance manual.
(4) If both flap inboard carriages have been
replaced following EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70–
138, dated March 2006, no further action is
required. Make an entry in the logbook to
show compliance with this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(f) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Staff,
FAA, Small Airplane Directorate, ATTN:
Albert J. Mercado, Aerospace Engineer, 901
Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4119; fax: (816)
329–4090, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(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.
Related Information
´ ´
(h) Refer to MCAI Direction generale de
l’aviation civile AD No. F–2005–017, Issue
date: January 19, 2005, for related
information.
Material Incorporated by Reference
(i) You must use EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70–
122, Amendment 1, dated March 2006, or
EADS SOCATA TBM Aircraft Mandatory
Service Bulletin SB 70–122, Amendment 2,
PO 00000
Frm 00047
Fmt 4700
Sfmt 4700
12077
dated January 2007, 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
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact EADS SOCATA, Direction
des Services, 65921 Tarbes Cedex 9, France;
telephone: 33 (0)5 62 41 73 00; fax: 33 (0)5
62 41 76 54; or SOCATA AIRCRAFT, INC.,
North Perry Airport, 7501 South Airport Rd.,
Pembroke Pines, FL 33023; telephone: (954)
893–1400; fax: (954) 964–4141.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; 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 Kansas City, Missouri, on March
6, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–4383 Filed 3–14–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27360; Directorate
Identifier 2007–NM–026–AD; Amendment
39–14986; AD 2007–06–05]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320 and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: 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
product. The MCAI describes the unsafe
condition as:
*
*
*
*
*
* * * updates [to the airplane maintenance
manual (AMM), engine service manual
(ESM), and quick engine change kit
instruction manual (QECKIM)] have
inadvertently introduced torque value errors
for the bolts that attach the forward engine
mount to the engine. * * *
*
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*
*
15MRR1
*
*
12078
Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations
Application of the incorrect torque to
the forward engine mount bolts during
maintenance could result in failure of
the forward engine mount and possible
separation of the engine from the
airplane and damage to the wing or loss
of control of the airplane. This AD
requires actions that are intended to
address the unsafe condition described
in the MCAI.
DATES: This AD becomes effective
March 30, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications, listed in the AD,
as of March 30, 2007.
We must receive comments on this
AD by April 16, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2141;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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Streamlined Issuance of AD
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
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14:08 Mar 14, 2007
Jkt 211001
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
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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2007–0036R1,
dated February 27, 2007 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
From May 2006, the forward engine mount
removal and installation procedures (AMM,
ESM, QECKIM) have been updated to add
removal and installation of the support
assemblies.
These updates have inadvertently
introduced torque value errors for the bolts
that attach the forward engine mount to the
engine. This condition, if not corrected, may
have the following consequences:
—rupture of bolts and failure of the support
assembly due to overtorqued bolts;
—reduced safe life of the secondary thrust
load path due to low torque on monoball
housing bolts.
Application of the incorrect torque to
the forward engine mount bolts during
maintenance could result in failure of
the forward engine mount and possible
separation of the engine from the
airplane and damage to the wing or loss
of control of the airplane. The MCAI
requires inspection, replacement, and
re-torque of the affected bolts and
adjustment of the torque values. You
may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued All Operators Telex
A320–71A1042, Revision 01, dated
February 12, 2007. Goodrich has issued
All Operators Letter CFM56–074,
Revision 1, dated February 1, 2007. The
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
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Fmt 4700
Sfmt 4700
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between the 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 FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because application of the incorrect
torque to the engine mount primary and
secondary load path bolts during
maintenance could result in failure of
the forward engine mount and possible
separation of the engine from the
airplane and damage to the wing or loss
of control of the airplane. Therefore, we
determined that notice and opportunity
for public comment before issuing this
AD are impracticable and that good
cause exists for making this amendment
effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2007–27360;
Directorate Identifier 2007–NM–026–
AD’’ at the beginning of your comments.
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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this AD.
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 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.
VerDate Aug<31>2005
14:08 Mar 14, 2007
Jkt 211001
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 FAA amends § 39.13 by adding
the following new AD:
I
2007–06–05 Airbus: Amendment 39–14986.
Docket No. FAA–2007–27360;
Directorate Identifier 2007–NM–026–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective March 30, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318–
111 and –112; A319–111, –112, –113, –114,
and –115; A320–111, –211, –212, and –214;
and A321–111, –112, –211, –212, and –213
airplanes; certificated in any category; all
serial numbers, which have CFM
International CFM56–5A or CFM56–5B series
engines installed.
Subject
(d) Powerplant.
Reason
(e) The mandatory continued airworthiness
information (MCAI) states:
From May 2006, the forward engine mount
removal and installation procedures (airplane
maintenance manual (AMM), engine service
manual (ESM), quick engine change kit
instruction manual (QECKIM)) have been
updated to add removal and installation of
the support assemblies.
These updates have inadvertently
introduced torque value errors for the bolts
that attach the forward engine mount to the
engine. This condition, if not corrected, may
have the following consequences:
—rupture of bolts and failure of the support
assembly due to overtorqued bolts;
—reduced safe life of the secondary thrust
load path due to low torque on monoball
housing bolts.
Application of the incorrect torque to the
forward engine mount bolts during
maintenance could result in failure of the
forward engine mount and possible
separation of the engine from the airplane
and damage to the wing or loss of control of
the airplane. The MCAI requires inspection,
replacement, and re-torque of the affected
bolts and adjustment of the torque values.
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Frm 00049
Fmt 4700
Sfmt 4700
12079
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) As of the effective date of this AD:
(i) Any maintenance on the engine mounts
must be performed in accordance with
correct instructions as identified in the
Airbus All Operators Telex (AOT) A320–
71A1042, Revision 01, dated February 12,
2007; or Goodrich All Operators Letter (AOL)
CFM56–074, Revision 1, dated February 1,
2007; and
(ii) Any forward engine mount support
assemblies fitted on an engine which is used
as replacement must be fitted in accordance
with correct instructions as identified in
Airbus AOT A320–71A1042, Revision 01,
dated February 12, 2007; or Goodrich AOL
CFM56–074, Revision 1, dated February 1,
2007.
(2) For aircraft on which any forward
engine mount support assembly has been
installed or maintained since May 2006 using
erroneous torque values given in the
maintenance data identified in paragraph 1.
of the Airbus AOT A320–71A1042, Revision
01, dated February 12, 2007, or where the use
of correct torque values cannot be
established: Within 20 days after the effective
date of this AD, accomplish the actions in
paragraphs (f)(2)(i), (f)(2)(ii), (f)(2)(iii), and
(f)(2)(iv) of this AD, as applicable, in
accordance with the instructions of Airbus
AOT A320–71A1042, Revision 01, dated
February 12, 2007. Aircraft on which no
engine removal has been performed since
aircraft delivery are not affected by this
paragraph. The alternative procedure given
in paragraph 4.2.3 of the AOT is acceptable,
provided that the nominal torque values
specified in paragraphs 4.2.1 and 4.2.2 are
restored within 120 flight cycles after
accomplishing paragraph 4.2.3 of the AOT.
(i) Remove and inspect the following
forward engine mount bolts: 77710–5H6
(AMM item 90) and NAS2815C15H (AMM
item 85).
(ii) If any bolts, 77710–5H6 (AMM item
90), are found broken during the above
inspection, before further flight, replace the
affected forward engine mount support
assembly (AMM item 75).
(iii) Replace bolts, 77710–5H6 (AMM item
90) and NAS2815C15H (AMM item 85), with
new items and torque them to the correct
value.
(iv) Re-torque 77458–7H21 bolts (AMM
item 95) and NAS2816C7H (AMM item 50)
to the correct value.
(3) Actions done before the effective date
of this AD in accordance with Airbus AOT
A320–71A1042, dated February 5, 2007, are
acceptable for compliance with the
corresponding provisions of paragraph (f)(2)
of this AD.
(4) Within 7 days after the inspection,
report all findings to Airbus Customer
Services, Engineering and Technical Support,
Attention: Mr. J-P Pourtau SEE11; telephone
+33 (0) 5 62 11 04 48; fax +33 (0) 5 61 93
36 14.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
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15MRR1
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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations
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, 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: Tim Dulin,
Aerospace Engineer, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2141; fax (425) 227–1149. 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.
(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.
Issued in Renton, Washington, on March 7,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–4535 Filed 3–14–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2006–26396; Airspace
Docket No. 06–AAL–40]
Revision of Class E Airspace; Red
Dog, AK
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2007–0036R1, dated February 27,
2007; Airbus All Operators Telex A320–
71A1042, Revision 01, dated February 12,
2007; and Goodrich All Operators Letter
CFM56–074, Revision 1, dated February 1,
2007, for related information.
SUMMARY: This action revises Class E
airspace at Red Dog, AK. Two new Area
Navigation (RNAV) Required Navigation
Performance (RNP) Special Instrument
Approach Procedures (SIAPs) and an
RNAV RNP Special Departure
Procedure (DP) are being developed for
the Red Dog Airport. This rule results in
the revision of Class E airspace upward
from 700 feet (ft.) and 1,200 ft. above the
surface near the Red Dog Airport, Red
Dog, AK.
DATES: Effective Dates: 0901 UTC, May
10, 2007, the Director of the Federal
Register approves this incorporation by
reference action under title 1, Code of
Federal Regulations, part 51, subject to
the annual revision of FAA Order
7400.9 and publication of conforming
amendments.
Material Incorporated by Reference
FOR FURTHER INFORMATION CONTACT:
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Related Information
(i) You must use Airbus All Operators
Telex A320–71A1042, Revision 01, dated
February 12, 2007; or Goodrich All Operators
Letter CFM56–074, Revision 1, dated
February 1, 2007; as applicable; 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
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, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
(3) 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/ibrlocations.html.
VerDate Aug<31>2005
14:08 Mar 14, 2007
Jkt 211001
Gary
Rolf, AAL–538G, Federal Aviation
Administration, 222 West 7th Avenue,
Box 14, Anchorage, AK 99513–7587;
telephone number (907) 271–5898; fax:
(907) 271–2850; e-mail:
gary.ctr.rolf@faa.gov. Internet address:
https://www.alaska.faa.gov/at.
SUPPLEMENTARY INFORMATION:
History
On Monday, December 18, 2006, the
FAA proposed to amend part 71 of the
Federal Aviation Regulations (14 CFR
part 71) to revise Class E airspace
upward from 700 ft. and 1,200 ft. above
the surface at Red Dog, AK (71 FR
75686). The action was proposed in
order to create Class E airspace
sufficient in size to contain aircraft
while executing two new SIAPs, and
one new DP for the Red Dog Airport.
The new Special approaches are (1) The
RNAV RNP Runway (RWY) 05, and (2)
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Fmt 4700
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the RNAV RNP RWY 20. The Special DP
is the IHOPO ONE RNAV RNP
Departure. Class E controlled airspace
extending upward from 700 ft. and
1,200 ft. above the surface in the Red
Dog Airport area is revised by this
action.
Interested parties were invited to
participate in this proposed rulemaking
by submitting written comments on the
proposal to the FAA. No comments have
been received, thus the rule is adopted
as proposed.
The area will be depicted on
aeronautical charts for pilot reference.
The coordinates for this airspace docket
are based on North American Datum 83.
The Class E airspace areas designated as
700/1,200 ft. transition areas are
published in paragraph 6005 of FAA
Order 7400.9P, Airspace Designations
and Reporting Points, dated September
1, 2006, and effective September 15,
2006, which is incorporated by
reference in 14 CFR 71.1. The Class E
airspace designation listed in this
document will be published
subsequently in the Order.
The Rule
This amendment to 14 CFR part 71
revises Class E airspace at the Red Dog
Airport, Alaska. This Class E airspace is
revised to accommodate aircraft
executing two new Special SIAPs, and
one new Special DP, and will be
depicted on aeronautical charts for pilot
reference. The intended effect of this
rule is to provide adequate controlled
airspace for Instrument Flight Rule (IFR)
operations at the Red Dog airport, Red
Dog, Alaska.
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. It, therefore—(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)
does not warrant preparation of a
regulatory evaluation as the anticipated
impact is so minimal. Since this a
routine matter that will only affect air
traffic procedures and air navigation, it
is certified that this rule will not have
a significant economic impact on a
substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
Subtitle 1, Section 106 describes the
authority of the FAA Administrator.
Subtitle VII, Aviation Programs,
E:\FR\FM\15MRR1.SGM
15MRR1
]]>Agencies
[Federal Register Volume 72, Number 50 (Thursday, March 15, 2007)]
[Rules and Regulations]
[Pages 12077-12080]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-4535]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27360; Directorate Identifier 2007-NM-026-AD;
Amendment 39-14986; AD 2007-06-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320 and A321
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: 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 product. The MCAI describes the unsafe condition as:
* * * * *
* * * updates [to the airplane maintenance manual (AMM), engine
service manual (ESM), and quick engine change kit instruction manual
(QECKIM)] have inadvertently introduced torque value errors for the
bolts that attach the forward engine mount to the engine. * * *
* * * * *
[[Page 12078]]
Application of the incorrect torque to the forward engine mount bolts
during maintenance could result in failure of the forward engine mount
and possible separation of the engine from the airplane and damage to
the wing or loss of control of the airplane. This AD requires actions
that are intended to address the unsafe condition described in the
MCAI.
DATES: This AD becomes effective March 30, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications, listed in the AD, as of March 30,
2007.
We must receive comments on this AD by April 16, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: https://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Management Facility between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (telephone (800) 647-5227) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
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 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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2007-0036R1, dated February 27, 2007 (referred
to after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
From May 2006, the forward engine mount removal and installation
procedures (AMM, ESM, QECKIM) have been updated to add removal and
installation of the support assemblies.
These updates have inadvertently introduced torque value errors
for the bolts that attach the forward engine mount to the engine.
This condition, if not corrected, may have the following
consequences:
--rupture of bolts and failure of the support assembly due to
overtorqued bolts;
--reduced safe life of the secondary thrust load path due to low
torque on monoball housing bolts.
Application of the incorrect torque to the forward engine mount bolts
during maintenance could result in failure of the forward engine mount
and possible separation of the engine from the airplane and damage to
the wing or loss of control of the airplane. The MCAI requires
inspection, replacement, and re-torque of the affected bolts and
adjustment of the torque values. You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued All Operators Telex A320-71A1042, Revision 01,
dated February 12, 2007. Goodrich has issued All Operators Letter
CFM56-074, Revision 1, dated February 1, 2007. The actions described in
this service information are intended to correct the unsafe condition
identified in the MCAI.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between the 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 FAA policies. Any such differences are
highlighted in a NOTE within the AD.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
application of the incorrect torque to the engine mount primary and
secondary load path bolts during maintenance could result in failure of
the forward engine mount and possible separation of the engine from the
airplane and damage to the wing or loss of control of the airplane.
Therefore, we determined that notice and opportunity for public comment
before issuing this AD are impracticable and that good cause exists for
making this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2007-27360; Directorate
Identifier 2007-NM-026-AD'' at the beginning of your comments.
[[Page 12079]]
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive about this AD.
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.
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 adding the following new AD:
2007-06-05 Airbus: Amendment 39-14986. Docket No. FAA-2007-27360;
Directorate Identifier 2007-NM-026-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
30, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318-111 and -112; A319-111,
-112, -113, -114, and -115; A320-111, -211, -212, and -214; and
A321-111, -112, -211, -212, and -213 airplanes; certificated in any
category; all serial numbers, which have CFM International CFM56-5A
or CFM56-5B series engines installed.
Subject
(d) Powerplant.
Reason
(e) The mandatory continued airworthiness information (MCAI)
states:
From May 2006, the forward engine mount removal and installation
procedures (airplane maintenance manual (AMM), engine service manual
(ESM), quick engine change kit instruction manual (QECKIM)) have
been updated to add removal and installation of the support
assemblies.
These updates have inadvertently introduced torque value errors
for the bolts that attach the forward engine mount to the engine.
This condition, if not corrected, may have the following
consequences:
--rupture of bolts and failure of the support assembly due to
overtorqued bolts;
--reduced safe life of the secondary thrust load path due to low
torque on monoball housing bolts.
Application of the incorrect torque to the forward engine mount
bolts during maintenance could result in failure of the forward
engine mount and possible separation of the engine from the airplane
and damage to the wing or loss of control of the airplane. The MCAI
requires inspection, replacement, and re-torque of the affected
bolts and adjustment of the torque values.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) As of the effective date of this AD:
(i) Any maintenance on the engine mounts must be performed in
accordance with correct instructions as identified in the Airbus All
Operators Telex (AOT) A320-71A1042, Revision 01, dated February 12,
2007; or Goodrich All Operators Letter (AOL) CFM56-074, Revision 1,
dated February 1, 2007; and
(ii) Any forward engine mount support assemblies fitted on an
engine which is used as replacement must be fitted in accordance
with correct instructions as identified in Airbus AOT A320-71A1042,
Revision 01, dated February 12, 2007; or Goodrich AOL CFM56-074,
Revision 1, dated February 1, 2007.
(2) For aircraft on which any forward engine mount support
assembly has been installed or maintained since May 2006 using
erroneous torque values given in the maintenance data identified in
paragraph 1. of the Airbus AOT A320-71A1042, Revision 01, dated
February 12, 2007, or where the use of correct torque values cannot
be established: Within 20 days after the effective date of this AD,
accomplish the actions in paragraphs (f)(2)(i), (f)(2)(ii),
(f)(2)(iii), and (f)(2)(iv) of this AD, as applicable, in accordance
with the instructions of Airbus AOT A320-71A1042, Revision 01, dated
February 12, 2007. Aircraft on which no engine removal has been
performed since aircraft delivery are not affected by this
paragraph. The alternative procedure given in paragraph 4.2.3 of the
AOT is acceptable, provided that the nominal torque values specified
in paragraphs 4.2.1 and 4.2.2 are restored within 120 flight cycles
after accomplishing paragraph 4.2.3 of the AOT.
(i) Remove and inspect the following forward engine mount bolts:
77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85).
(ii) If any bolts, 77710-5H6 (AMM item 90), are found broken
during the above inspection, before further flight, replace the
affected forward engine mount support assembly (AMM item 75).
(iii) Replace bolts, 77710-5H6 (AMM item 90) and NAS2815C15H
(AMM item 85), with new items and torque them to the correct value.
(iv) Re-torque 77458-7H21 bolts (AMM item 95) and NAS2816C7H
(AMM item 50) to the correct value.
(3) Actions done before the effective date of this AD in
accordance with Airbus AOT A320-71A1042, dated February 5, 2007, are
acceptable for compliance with the corresponding provisions of
paragraph (f)(2) of this AD.
(4) Within 7 days after the inspection, report all findings to
Airbus Customer Services, Engineering and Technical Support,
Attention: Mr. J-P Pourtau SEE11; telephone +33 (0) 5 62 11 04 48;
fax +33 (0) 5 61 93 36 14.
FAA AD Differences
Note: This AD differs from the MCAI and/ or service information
as follows: No differences.
[[Page 12080]]
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, 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: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-2141; fax (425) 227-1149. 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.
(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 European Aviation Safety Agency (EASA)
Airworthiness Directive 2007-0036R1, dated February 27, 2007; Airbus
All Operators Telex A320-71A1042, Revision 01, dated February 12,
2007; and Goodrich All Operators Letter CFM56-074, Revision 1, dated
February 1, 2007, for related information.
Material Incorporated by Reference
(i) You must use Airbus All Operators Telex A320-71A1042,
Revision 01, dated February 12, 2007; or Goodrich All Operators
Letter CFM56-074, Revision 1, dated February 1, 2007; as applicable;
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 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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
(3) 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 March 7, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-4535 Filed 3-14-07; 8:45 am]
BILLING CODE 4910-13-P
