Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 51164-51167 [E7-17385]
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51164
Federal Register / Vol. 72, No. 172 / Thursday, September 6, 2007 / Rules and Regulations
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or different compliance time for
this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(3) An AMOC approved previously in
accordance with AD 2005–18–14 is approved
as an AMOC for the corresponding
provisions of this AD.
Related Information
(n) European Aviation Safety Agency
airworthiness directive 2006–0114, dated
May 10, 2006, also addresses the subject of
this AD.
Material Incorporated by Reference
(o) You must use the service bulletins
identified in Table 1 of this AD to perform
the actions that are required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Dassault Service Bulletin F10–313, Revision
1, dated May 10, 2006, in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On September 26, 2005 (70 FR 53540,
September 9, 2005), the Director of the
Federal Register approved the incorporation
by reference of Dassault Alert Service
Bulletin F10–A312, Revision 1, dated June
27, 2005, including the Service Bulletins
Compliance Card.
(3) On April 26, 2005 (70 FR 18282, April
11, 2005), the Director of the Federal Register
approved the incorporation by reference of
Dassault Alert Service Bulletin F10–A312,
dated February 25, 2005, including the
Service Bulletins Compliance Card.
(4) Contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey 07606,
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/federalregister/cfr/ibr-locations.html.
TABLE 1.—SERVICE INFORMATION INCORPORATED BY REFERENCE
Service Bulletin
Revision level
Date
Dassault Alert Service Bulletin F10–A312, including the Service Bulletins Compliance Card ..............
Dassault Alert Service Bulletin F10–A312, including the Service Bulletins Compliance Card ..............
Dassault Service Bulletin F10–313 .........................................................................................................
Original ..................
Revision 1 ..............
Revision 1 ..............
February 25, 2005.
June 27, 2005.
May 10, 2006.
pwalker on PROD1PC71 with RULES
Issued in Renton, Washington, on August
17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–17288 Filed 9–5–07; 8:45 am]
support, and corrective action if
necessary; and a check of the NLG strut
inflation pressure, and an adjustment if
necessary. For some of these airplanes,
the existing AD also requires a revision
to the aircraft flight manual to
incorporate an operating procedure to
BILLING CODE 4910–13–P
recover normal steering in the event of
a steering failure. This new AD instead
DEPARTMENT OF TRANSPORTATION requires repetitive inspections of the
NLG upper support, and related
Federal Aviation Administration
investigative/corrective actions in
accordance with new service
14 CFR Part 39
information; and removes the one-time
inspection that was required by the
[Docket No. FAA–2007–27776; Directorate
existing AD. This new AD also provides
Identifier 2006–NM–170–AD; Amendment
an optional terminating action for the
39–15189; AD 2007–18–09]
repetitive inspections. This AD results
RIN 2120–AA64
from a report of an incident where an
airplane landed with the NLG turned 90
Airworthiness Directives; Airbus Model degrees from centerline, and from
A318, A319, A320, and A321 Airplanes
additional reports of NLG upper support
anti-rotation lugs rupturing in service.
AGENCY: Federal Aviation
We are issuing this AD to prevent
Administration (FAA), Department of
landings with the NLG turned 90
Transportation (DOT).
degrees from centerline, which could
ACTION: Final rule.
result in reduced controllability of the
airplane.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
DATES: This AD becomes effective
which applies to all Airbus Model
October 11, 2007.
The Director of the Federal Register
A318–100, A319–100, A320–200, A321–
100, and A321–200 series airplanes, and approved the incorporation by reference
of a certain publication listed in the AD
Model A320–111 airplanes. That AD
as of October 11, 2007.
currently requires an inspection to
On November 30, 2005 (70 FR 70715,
determine whether certain braking and
November 23, 2005), the Director of the
steering control units (BSCUs) are
Federal Register approved the
installed or have ever been installed.
incorporation by reference of a certain
For airplanes on which certain BSCUs
are installed or have ever been installed, publication listed in the AD.
the existing AD requires an inspection
ADDRESSES: You may examine the AD
of the nose landing gear (NLG) upper
docket on the Internet at https://
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18:26 Sep 05, 2007
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dms.dot.gov or in person at the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
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:
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 Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Operations office (telephone (800) 647–
5527) is located on the ground floor of
the West Building at the DOT 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 2005–24–06, amendment
39–14386 (70 FR 70715, November 23,
2005). The existing AD applies to all
Airbus Model A318–100, A319–100,
A320–200, A321–100, and A321–200
series airplanes, and Model A320–111
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Federal Register / Vol. 72, No. 172 / Thursday, September 6, 2007 / Rules and Regulations
airplanes. That NPRM was published in
the Federal Register on April 5, 2007
(72 FR 16749). That NPRM proposed to
continue to require an inspection to
determine whether certain braking and
steering control units (BSCUs) are
installed or have ever been installed.
For airplanes on which certain BSCUs
are installed or have ever been installed,
that NPRM proposed to continue to
require a revision to the aircraft flight
manual (AFM) to incorporate an
operating procedure to recover normal
steering in the event of a steering
failure. That NPRM also proposed to
require repetitive inspections of the
nose landing gear (NLG) upper support,
and related investigative/corrective
actions, and an optional terminating
action for the repetitive inspections.
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.
Support for the AD
The National Transportation Safety
Board supports the adoption of the AD.
Request To Revise ‘‘Optional
Terminating Action’’ Reference
Airbus requests that we rephrase the
heading of paragraph (l), ‘‘Optional
Terminating Action,’’ of the NPRM.
Airbus states that the terminating action
for the issue addressed by the NPRM is
not yet available. According to Airbus,
the terminating action will include
implementation of a new BSCU
standard, which is currently being
defined. Therefore, Airbus suggests that
instead of the title ‘‘Optional
Terminating Action,’’ we use a different
title, such as ‘‘Action that Renders Void
the Requirements of this AD,’’ or
equivalent wording. Airbus states that it
is correct to say that the actions
proposed in paragraph (l) of the NPRM
would render void the requirements of
this AD, and that no further action
would be required by this AD. However,
the terminating action for the issue will
require installation of a new future
BSCU standard. Airbus anticipates that
it will require the installation of the
future BSCU standard as a terminating
action.
We disagree with the request to
rephrase the title of paragraph (l) of this
AD. We consider the phrase ‘‘Action
that Renders Void the Requirements of
this AD,’’ to be equivalent to the
existing title ‘‘Optional Terminating
Action.’’ Furthermore, this AD is fully
consistent with European Aviation
Safety Agency (EASA) airworthiness
directive 2006–0174, dated June 21,
2006, which is the parallel EASA
airworthiness directive to this AD. If
EASA supersedes airworthiness
directive 2006–0174 for any reason, we
will consider additional rulemaking. We
have not changed the AD in this regard.
51165
Explanation of Editorial Change to
Paragraph (l)
Paragraph (l) of the NPRM referred to
‘‘standard L4.1 and L4.5.’’ That
paragraph should refer to ‘‘standard
L4.1 or L4.5.’’ We have revised
paragraph (l) of the final rule
accordingly. This change will not affect
accomplishment of the optional
terminating action.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
This AD affects about 720 airplanes of
U.S. registry. The following table
provides the estimated costs for U.S.
operators to comply with this AD. The
average labor rate is $80 per work hour.
ESTIMATED COSTS
Work hours
Records review (required by AD 2005–24–06) .............
AFM revision (required by AD 2005–24–06) .................
Special detailed inspection in accordance with new
service information (new action).
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Action
1 ..................
1 ..................
1 ..................
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
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Parts
Cost per airplane
None
None
None
$80 .....................................
$80 .....................................
$80, per inspection cycle ..
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;
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Fleet cost
$57,600.
$57,600.
$57,600, per inspection
cycle.
(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.
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Federal Register / Vol. 72, No. 172 / Thursday, September 6, 2007 / Rules and Regulations
not and never has been equipped with a
BSCU P/N E21327001 or P/N E21327003, no
further action is required by this AD.
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 39–14386 (70
FR 70715, November 23, 2005) and by
adding the following new airworthiness
directive (AD):
I
2007–18–09 AIRBUS: Amendment 39–
15189. Docket No. FAA–2007–27776;
Directorate Identifier 2006–NM–170–AD.
Effective Date
(a) This AD becomes effective October 11,
2007.
Affected ADs
(b) This AD supersedes AD 2005–24–06.
Applicability
(c) This AD applies to all Airbus Model
A318, A319, A320, and A321 airplanes.
Unsafe Condition
(d) This AD results from a report of an
incident where an airplane landed with the
nose landing gear (NLG) turned 90 degrees
from centerline, and from additional reports
of NLG upper support anti-rotation lugs
rupturing in service. We are issuing this AD
to prevent landings with the NLG turned 90
degrees from centerline, which could result
in reduced controllability of the airplane.
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.
pwalker on PROD1PC71 with RULES
Restatement of Certain Requirements of AD
2005–24–06
Records Review
(f) Within 5 days after November 30, 2005
(the effective date of AD 2005–24–06),
perform a records review to determine
whether the airplane is equipped with or has
ever been equipped with an enhanced
manufacturing and maintainability (EMM)
braking and steering control unit (BSCU) part
number (P/N) E21327001 (standard L4.1,
installed by Airbus Modification 26965, or
Airbus Service Bulletin A320–32–1912) or
P/N E21327003 (standard L4.5, installed by
Airbus Modification 33376, or Airbus Service
Bulletin A320–32–1261). Airbus Service
Bulletin A320–32–1310, dated February 8,
2006, is one approved method for doing the
records review.
(g) For airplanes on which a records review
required by paragraph (f) of this AD
conclusively determines that the airplane is
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Airplane Flight Manual (AFM) Revision
(h) For airplanes that are not specified in
paragraph (g) of this AD and on which Airbus
Modification 31152 has not been
incorporated in production (i.e., applicable
only to aircraft with steering powered by the
green hydraulic system): Within 10 days after
November 30, 2005, revise the Limitation
Section of the Airbus A318/319/320/321
Aircraft Flight Manual (AFM) to include the
following information. This may be done by
inserting a copy of this AD into the AFM:
‘‘The ECAM message, in case of a nose
wheel steering failure, will be worded as
follows:
—‘‘WHEEL N/W STRG FAULT’’ for aircraft
with the FWC E3 and subsequent standards
—‘‘WHEEL N.W. STEER FAULT’’ for aircraft
with the FWC E2 Standard.
I If the L/G SHOCK ABSORBER FAULT
ECAM caution is triggered at any time in
flight, and the WHEEL N/W STRG FAULT
ECAM caution is triggered after the landing
gear extension:
• When all landing gear doors are
indicated closed on ECAM WHEEL page,
reset the BSCU:
—A/SKID&N/W STRG—OFF THEN ON
• If the WHEEL N/W STRG FAULT ECAM
caution is no longer displayed, this indicates
a successful nose wheel re-centering and
steering recovery.
—Rearm the AUTO BRAKE, if necessary.
• If the WHEEL N/W STRG FAULT ECAM
caution remains displayed, this indicates that
the nose wheel steering remains lost, and that
the nose wheels are not centered.
—During landing, delay nose wheel
touchdown for as long as possible.
—Refer to the ECAM STATUS.
I If the WHEEL N/W STRG FAULT ECAM
caution appears, without the L/G SHOCK
ABSORBER FAULT ECAM caution:
—No specific crew action is requested by the
WHEEL N/W STRG FAULT ECAM caution
procedure.
—Refer to the ECAM STATUS.’’
Note 1: When a statement identical to that
in paragraph (h) of this AD has been included
in the general revisions of the AFM, the
general revisions may be inserted into the
AFM, and the copy of this AD may be
removed from the AFM.
New Requirements of This AD
Inspection Thresholds
(i) For airplanes that are not specified in
paragraph (g) of this AD, at the earlier of the
times specified in paragraphs (i)(1) and (i)(2)
of this AD: Do a special detailed inspection
(boroscopic) for broken or cracked NLG
upper support lugs and missing cylinder
lugs, and do all applicable related
investigative/corrective actions before further
flight. Do all actions in accordance with
Airbus Technical Note 957.1901/05, dated
October 18, 2005; or the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1310, dated February 8, 2006. After the
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effective date of this AD, only Airbus Service
Bulletin A320–32–1310, dated February 8,
2006, may be used. Where the service
bulletin specifies that restoring the NLG is
necessary in accordance with Airbus
recommendations, this AD requires restoring
the NLG in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
Safety Agency (EASA) (or its delegated
agent). Repeat the inspection thereafter at the
applicable interval specified in paragraph (j)
or (k) of this AD.
(1) Within 100 flight cycles following an
electronic centralized aircraft monitoring
(ECAM) caution ‘‘L/G SHOCK ABSORBER
FAULT’’ associated with at least one of the
following centralized fault display system
(CFDS) messages specified in paragraph
(i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD.
(i) ‘‘N L/G EXT PROX SNSR 24GA TGT
POS.’’
(ii) ‘‘N L/G EXT PROX SNSR 25GA TGT
POS.’’
(iii) ‘‘N L/G SHOCK ABSORBER FAULT
2526GM.’’
(2) At the later of the times specified in
paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Within 20 months, 6,000 flight hours, or
4,500 flight cycles since the date of issuance
of the original French standard airworthiness
certificate, or the original French export
certificate of airworthiness, whichever occurs
first.
(ii) Within 6 months, 1,800 flight hours, or
1,350 flight cycles after the effective date of
this AD, whichever occurs first.
Repetitive Inspection Intervals
(j) For airplanes not specified in paragraph
(g) of this AD that are equipped with EMM
BSCU standard L4.1 or L4.5: Repeat the
inspection specified in paragraph (i) of this
AD thereafter at intervals not to exceed the
earliest of 6 months; 1,800 flight hours; 1,350
flight cycles; or 100 flight cycles following
certain ECAM cautions and CFDS messages,
as specified in paragraph (i)(1) of this AD.
(k) For airplanes not specified in paragraph
(g) of this AD that are equipped with EMM
BSCU standard L4.8 or a non-EMM BSCU:
Repeat the inspection specified in paragraph
(i) of this AD thereafter at intervals not to
exceed the earliest of 20 months; 6,000 flight
hours; 4,500 flight cycles; or 100 flight cycles
following certain ECAM cautions and CFDS
messages, as specified in paragraph (i)(1) of
this AD.
Note 2: For the purposes of this AD, a
special detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. The examination is likely to
make extensive use of specialized inspection
techniques and/or equipment. Intricate
cleaning and substantial access or
disassembly procedure may be required.’’
Optional Terminating Action
(l) For airplanes that are not specified in
paragraph (g) of this AD: Installation of an
NLG with new upper support anti-rotation
lugs and new cylinder lugs, or installation of
an NLG that was never driven by EMM BSCU
standard L4.1 or L4.5; combined with
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Federal Register / Vol. 72, No. 172 / Thursday, September 6, 2007 / Rules and Regulations
installation of an EMM BSCU standard L4.8
or a non–EMM BSCU; constitutes terminating
action for the requirements of this AD. Do the
installations in accordance with a method
approved by either the Manager,
International Branch, ANM–116; or the
EASA (or its delegated agent). Chapter 32 of
the Airbus A318/A319/A320/A321 Aircraft
Maintenance Manual (AMM) is one approved
method for doing the installations.
No Report Required
(m) Although Airbus Service Bulletin
A320–32–1310, dated February 8, 2006,
specifies sending certain inspection results to
Airbus, this AD does not include that
requirement.
Credit Paragraph
(n) Inspections done before the effective
date of this AD in accordance with Chapter
12, Subject 12–14–32 of the Airbus A318/
A319/A320/A321 AMM, as revised by Airbus
A318/A319/A320/A321 AMM Temporary
Revision 12–001, dated November 13, 2005,
are acceptable for compliance with the
requirements of paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
pwalker on PROD1PC71 with RULES
Related Information
(p) EASA airworthiness directive 2006–
0174, dated June 21, 2006, also addresses the
subject of this AD.
Material Incorporated by Reference
(q) You must use Airbus Technical Note
957.1901/05, dated October 18, 2005; or
Airbus Service Bulletin A320–32–1310,
dated February 8, 2006; as applicable, to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Airbus Service Bulletin A320–32–1310,
dated February 8, 2006, in accordance with
5 U.S.C. 552(a) and 1 CFR part 51.
(2) On November 30, 2005 (70 FR 70715,
November 23, 2005), the Director of the
Federal Register approved the incorporation
by reference of Airbus Technical Note
957.1901/05, dated October 18, 2005.
(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.
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51167
Issued in Renton, Washington, on August
17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–17385 Filed 9–5–07; 8:45 am]
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4145; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
BILLING CODE 4910–13–P
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 July 16, 2007 (72 FR 38800).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27975 Directorate
Identifier 2007–CE–041–AD; Amendment
39–15187; AD 2007–18–07]
RIN 2120–AA64
Airworthiness Directives; Piaggio Aero
Industries S.p.A. Model P–180
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued 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:
Several aircraft, at the factory, presented
some debris in the hydraulic fluid of the
steering system. Investigations revealed that
some components of the steering system can
be responsible for the fluid contamination
because of an initial pollution on their
manufacturing.
If not corrected, a contaminated fluid could
cause malfunction and a possible jamming of
the steering system.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
October 11, 2007.
On October 11, 2007, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at Document
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
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Discussion
Several aircraft, at the factory, presented
some debris in the hydraulic fluid of the
steering system. Investigations revealed that
some components of the steering system can
be responsible for the fluid contamination
because of an initial pollution on their
manufacturing.
If not corrected, a contaminated fluid could
cause malfunction and a possible jamming of
the steering system.
The superseded Airworthiness Directive
(AD) 2007–0088–E was previously issued to
address the unsafe condition.
The present Airworthiness Directive
expands applicability of this AD to all P.180
‘Avanti’ series aircraft and the list of
defective components as listed in revision 1
of Piaggio Aero Industries Mandatory Service
Bulletin No 80–0236. This AD also requires
Temporary Changes to the respective
Airplane Flight Manual (AFM) and Aircraft
Maintenance Manual (AMM) and introduces
procedures to recondition defective units.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Comment Issue: Replacement of Nose
Landing Gear
One commenter suggests that the nose
landing gear (NLG) does not need to be
replaced as required in paragraph
(f)(2)(ii) of this AD, but rather the
steering actuator and manifold mounted
to the NLG need to be replaced.
We agree with the commenter that it
is the steering actuator and the manifold
that need to be replaced and not the
entire NLG. However, the service
bulletin requires removing and sending
the original NLG to a Messier-Dowty
engineer to do the actuator and
manifold replacement. The service
bulletin then requires installing a
serviceable NLG. The replacement NLG
could be the original, which has been
rebuilt according to Annex 8 of Piaggio
Aero Industries S.p.A. Service Bulletin
(Mandatory) N.: 80–0236 Rev. 1, dated
May 15, 2007 (Messier-Dowty Service
Bulletin No. P180–32–24, dated May 15,
2007), or it could be an exchanged NLG
that complies with this AD. We have
E:\FR\FM\06SER1.SGM
06SER1
]]>Agencies
[Federal Register Volume 72, Number 172 (Thursday, September 6, 2007)]
[Rules and Regulations]
[Pages 51164-51167]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-17385]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27776; Directorate Identifier 2006-NM-170-AD;
Amendment 39-15189; AD 2007-18-09]
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.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to all Airbus Model A318-100, A319-100, A320-200,
A321-100, and A321-200 series airplanes, and Model A320-111 airplanes.
That AD currently requires an inspection to determine whether certain
braking and steering control units (BSCUs) are installed or have ever
been installed. For airplanes on which certain BSCUs are installed or
have ever been installed, the existing AD requires an inspection of the
nose landing gear (NLG) upper support, and corrective action if
necessary; and a check of the NLG strut inflation pressure, and an
adjustment if necessary. For some of these airplanes, the existing AD
also requires a revision to the aircraft flight manual to incorporate
an operating procedure to recover normal steering in the event of a
steering failure. This new AD instead requires repetitive inspections
of the NLG upper support, and related investigative/corrective actions
in accordance with new service information; and removes the one-time
inspection that was required by the existing AD. This new AD also
provides an optional terminating action for the repetitive inspections.
This AD results from a report of an incident where an airplane landed
with the NLG turned 90 degrees from centerline, and from additional
reports of NLG upper support anti-rotation lugs rupturing in service.
We are issuing this AD to prevent landings with the NLG turned 90
degrees from centerline, which could result in reduced controllability
of the airplane.
DATES: This AD becomes effective October 11, 2007.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 11,
2007.
On November 30, 2005 (70 FR 70715, November 23, 2005), the Director
of the Federal Register approved the incorporation by reference of a
certain publication listed in the AD.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue, SE., Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
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:
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 Operations
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Operations office (telephone (800) 647-5527) is
located on the ground floor of the West Building at the DOT 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 2005-24-06, amendment
39-14386 (70 FR 70715, November 23, 2005). The existing AD applies to
all Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200
series airplanes, and Model A320-111
[[Page 51165]]
airplanes. That NPRM was published in the Federal Register on April 5,
2007 (72 FR 16749). That NPRM proposed to continue to require an
inspection to determine whether certain braking and steering control
units (BSCUs) are installed or have ever been installed. For airplanes
on which certain BSCUs are installed or have ever been installed, that
NPRM proposed to continue to require a revision to the aircraft flight
manual (AFM) to incorporate an operating procedure to recover normal
steering in the event of a steering failure. That NPRM also proposed to
require repetitive inspections of the nose landing gear (NLG) upper
support, and related investigative/corrective actions, and an optional
terminating action for the repetitive inspections.
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.
Support for the AD
The National Transportation Safety Board supports the adoption of
the AD.
Request To Revise ``Optional Terminating Action'' Reference
Airbus requests that we rephrase the heading of paragraph (l),
``Optional Terminating Action,'' of the NPRM. Airbus states that the
terminating action for the issue addressed by the NPRM is not yet
available. According to Airbus, the terminating action will include
implementation of a new BSCU standard, which is currently being
defined. Therefore, Airbus suggests that instead of the title
``Optional Terminating Action,'' we use a different title, such as
``Action that Renders Void the Requirements of this AD,'' or equivalent
wording. Airbus states that it is correct to say that the actions
proposed in paragraph (l) of the NPRM would render void the
requirements of this AD, and that no further action would be required
by this AD. However, the terminating action for the issue will require
installation of a new future BSCU standard. Airbus anticipates that it
will require the installation of the future BSCU standard as a
terminating action.
We disagree with the request to rephrase the title of paragraph (l)
of this AD. We consider the phrase ``Action that Renders Void the
Requirements of this AD,'' to be equivalent to the existing title
``Optional Terminating Action.'' Furthermore, this AD is fully
consistent with European Aviation Safety Agency (EASA) airworthiness
directive 2006-0174, dated June 21, 2006, which is the parallel EASA
airworthiness directive to this AD. If EASA supersedes airworthiness
directive 2006-0174 for any reason, we will consider additional
rulemaking. We have not changed the AD in this regard.
Explanation of Editorial Change to Paragraph (l)
Paragraph (l) of the NPRM referred to ``standard L4.1 and L4.5.''
That paragraph should refer to ``standard L4.1 or L4.5.'' We have
revised paragraph (l) of the final rule accordingly. This change will
not affect accomplishment of the optional terminating action.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
This AD affects about 720 airplanes of U.S. registry. The following
table provides the estimated costs for U.S. operators to comply with
this AD. The average labor rate is $80 per work hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Work hours Parts Cost per airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Records review (required by AD 1.................... None $80................. $57,600.
2005-24-06).
AFM revision (required by AD 2005- 1.................... None $80................. $57,600.
24-06).
Special detailed inspection in 1.................... None $80, per inspection $57,600, per
accordance with new service cycle. inspection cycle.
information (new action).
----------------------------------------------------------------------------------------------------------------
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.
[[Page 51166]]
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 39-14386 (70 FR 70715, November 23, 2005) and by
adding the following new airworthiness directive (AD):
2007-18-09 AIRBUS: Amendment 39-15189. Docket No. FAA-2007-27776;
Directorate Identifier 2006-NM-170-AD.
Effective Date
(a) This AD becomes effective October 11, 2007.
Affected ADs
(b) This AD supersedes AD 2005-24-06.
Applicability
(c) This AD applies to all Airbus Model A318, A319, A320, and
A321 airplanes.
Unsafe Condition
(d) This AD results from a report of an incident where an
airplane landed with the nose landing gear (NLG) turned 90 degrees
from centerline, and from additional reports of NLG upper support
anti-rotation lugs rupturing in service. We are issuing this AD to
prevent landings with the NLG turned 90 degrees from centerline,
which could result in reduced controllability of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD 2005-24-06
Records Review
(f) Within 5 days after November 30, 2005 (the effective date of
AD 2005-24-06), perform a records review to determine whether the
airplane is equipped with or has ever been equipped with an enhanced
manufacturing and maintainability (EMM) braking and steering control
unit (BSCU) part number (P/N) E21327001 (standard L4.1, installed by
Airbus Modification 26965, or Airbus Service Bulletin A320-32-1912)
or P/N E21327003 (standard L4.5, installed by Airbus Modification
33376, or Airbus Service Bulletin A320-32-1261). Airbus Service
Bulletin A320-32-1310, dated February 8, 2006, is one approved
method for doing the records review.
(g) For airplanes on which a records review required by
paragraph (f) of this AD conclusively determines that the airplane
is not and never has been equipped with a BSCU P/N E21327001 or P/N
E21327003, no further action is required by this AD.
Airplane Flight Manual (AFM) Revision
(h) For airplanes that are not specified in paragraph (g) of
this AD and on which Airbus Modification 31152 has not been
incorporated in production (i.e., applicable only to aircraft with
steering powered by the green hydraulic system): Within 10 days
after November 30, 2005, revise the Limitation Section of the Airbus
A318/319/320/321 Aircraft Flight Manual (AFM) to include the
following information. This may be done by inserting a copy of this
AD into the AFM:
``The ECAM message, in case of a nose wheel steering failure,
will be worded as follows:
?>--``WHEEL N/W STRG FAULT'' for aircraft with the FWC E3 and
subsequent standards
--``WHEEL N.W. STEER FAULT'' for aircraft with the FWC E2 Standard.
[squarf] If the L/G SHOCK ABSORBER FAULT ECAM caution is
triggered at any time in flight, and the WHEEL N/W STRG FAULT ECAM
caution is triggered after the landing gear extension:
When all landing gear doors are indicated closed on
ECAM WHEEL page, reset the BSCU:
--A/SKID&N/W STRG--OFF THEN ON
If the WHEEL N/W STRG FAULT ECAM caution is no longer
displayed, this indicates a successful nose wheel re-centering and
steering recovery.
--Rearm the AUTO BRAKE, if necessary.
If the WHEEL N/W STRG FAULT ECAM caution remains
displayed, this indicates that the nose wheel steering remains lost,
and that the nose wheels are not centered.
--During landing, delay nose wheel touchdown for as long as
possible.
--Refer to the ECAM STATUS.
[squarf] If the WHEEL N/W STRG FAULT ECAM caution appears,
without the L/G SHOCK ABSORBER FAULT ECAM caution:
--No specific crew action is requested by the WHEEL N/W STRG FAULT
ECAM caution procedure.
--Refer to the ECAM STATUS.''
Note 1: When a statement identical to that in paragraph (h) of
this AD has been included in the general revisions of the AFM, the
general revisions may be inserted into the AFM, and the copy of this
AD may be removed from the AFM.
New Requirements of This AD
Inspection Thresholds
(i) For airplanes that are not specified in paragraph (g) of
this AD, at the earlier of the times specified in paragraphs (i)(1)
and (i)(2) of this AD: Do a special detailed inspection (boroscopic)
for broken or cracked NLG upper support lugs and missing cylinder
lugs, and do all applicable related investigative/corrective actions
before further flight. Do all actions in accordance with Airbus
Technical Note 957.1901/05, dated October 18, 2005; or the
Accomplishment Instructions of Airbus Service Bulletin A320-32-1310,
dated February 8, 2006. After the effective date of this AD, only
Airbus Service Bulletin A320-32-1310, dated February 8, 2006, may be
used. Where the service bulletin specifies that restoring the NLG is
necessary in accordance with Airbus recommendations, this AD
requires restoring the NLG in accordance with a method approved by
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or
its delegated agent). Repeat the inspection thereafter at the
applicable interval specified in paragraph (j) or (k) of this AD.
(1) Within 100 flight cycles following an electronic centralized
aircraft monitoring (ECAM) caution ``L/G SHOCK ABSORBER FAULT''
associated with at least one of the following centralized fault
display system (CFDS) messages specified in paragraph (i)(1)(i),
(i)(1)(ii), or (i)(1)(iii) of this AD.
(i) ``N L/G EXT PROX SNSR 24GA TGT POS.''
(ii) ``N L/G EXT PROX SNSR 25GA TGT POS.''
(iii) ``N L/G SHOCK ABSORBER FAULT 2526GM.''
(2) At the later of the times specified in paragraphs (i)(2)(i)
and (i)(2)(ii) of this AD.
(i) Within 20 months, 6,000 flight hours, or 4,500 flight cycles
since the date of issuance of the original French standard
airworthiness certificate, or the original French export certificate
of airworthiness, whichever occurs first.
(ii) Within 6 months, 1,800 flight hours, or 1,350 flight cycles
after the effective date of this AD, whichever occurs first.
Repetitive Inspection Intervals
(j) For airplanes not specified in paragraph (g) of this AD that
are equipped with EMM BSCU standard L4.1 or L4.5: Repeat the
inspection specified in paragraph (i) of this AD thereafter at
intervals not to exceed the earliest of 6 months; 1,800 flight
hours; 1,350 flight cycles; or 100 flight cycles following certain
ECAM cautions and CFDS messages, as specified in paragraph (i)(1) of
this AD.
(k) For airplanes not specified in paragraph (g) of this AD that
are equipped with EMM BSCU standard L4.8 or a non-EMM BSCU: Repeat
the inspection specified in paragraph (i) of this AD thereafter at
intervals not to exceed the earliest of 20 months; 6,000 flight
hours; 4,500 flight cycles; or 100 flight cycles following certain
ECAM cautions and CFDS messages, as specified in paragraph (i)(1) of
this AD.
Note 2: For the purposes of this AD, a special detailed
inspection is: ``An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or
irregularity. The examination is likely to make extensive use of
specialized inspection techniques and/or equipment. Intricate
cleaning and substantial access or disassembly procedure may be
required.''
Optional Terminating Action
(l) For airplanes that are not specified in paragraph (g) of
this AD: Installation of an NLG with new upper support anti-rotation
lugs and new cylinder lugs, or installation of an NLG that was never
driven by EMM BSCU standard L4.1 or L4.5; combined with
[[Page 51167]]
installation of an EMM BSCU standard L4.8 or a non-EMM BSCU;
constitutes terminating action for the requirements of this AD. Do
the installations in accordance with a method approved by either the
Manager, International Branch, ANM-116; or the EASA (or its
delegated agent). Chapter 32 of the Airbus A318/A319/A320/A321
Aircraft Maintenance Manual (AMM) is one approved method for doing
the installations.
No Report Required
(m) Although Airbus Service Bulletin A320-32-1310, dated
February 8, 2006, specifies sending certain inspection results to
Airbus, this AD does not include that requirement.
Credit Paragraph
(n) Inspections done before the effective date of this AD in
accordance with Chapter 12, Subject 12-14-32 of the Airbus A318/
A319/A320/A321 AMM, as revised by Airbus A318/A319/A320/A321 AMM
Temporary Revision 12-001, dated November 13, 2005, are acceptable
for compliance with the requirements of paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(p) EASA airworthiness directive 2006-0174, dated June 21, 2006,
also addresses the subject of this AD.
Material Incorporated by Reference
(q) You must use Airbus Technical Note 957.1901/05, dated
October 18, 2005; or Airbus Service Bulletin A320-32-1310, dated
February 8, 2006; as applicable, to perform the actions that are
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Airbus Service Bulletin A320-32-1310,
dated February 8, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On November 30, 2005 (70 FR 70715, November 23, 2005), the
Director of the Federal Register approved the incorporation by
reference of Airbus Technical Note 957.1901/05, dated October 18,
2005.
(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 August 17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-17385 Filed 9-5-07; 8:45 am]
BILLING CODE 4910-13-P
