Airworthiness Directives; Airbus Model A300 Airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310 Airplanes, 60203-60206 [E8-24151]
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Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Proposed Rules
60203
Compliance
(e) To address this problem, you must do
the following, unless already done:
Actions
Compliance
Procedures
Install Stall Warning Heat Control Modification
Kit, Piper part number 88452–002.
Within the next 100 hours time-in-service after
the effective date of this AD.
As specified in Piper Mandatory Service Bulletin No. 1192, dated September 15, 2008,
following Drawing No. 88452 dated June
19, 2008.
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Atlanta Aircraft
Certification Office (ACO), 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: John
Lee, Aerospace Engineer, Federal Aviation
Administration, Atlanta ACO, One Crown
Center, 1895 Phoenix Blvd., Suite 450,
Atlanta, Georgia 30349; telephone: (770) 994–
6736; fax: (770) 703–6097. 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
(g) To get copies of the service information
referenced in this AD, contact Piper Aircraft,
Inc., 2926 Piper Drive, Vero Beach, Florida
32960; telephone: (772) 567–4361; fax: (772)
978–6573; Web site: https://
www.newpiper.com/. To view the AD docket,
go to U.S. Department of Transportation,
Docket Operations, M–30, West Building
Ground Floor, Room W12–140, 1200 New
Jersey Avenue, SE., Washington, DC 20590,
or on the Internet at https://
www.regulations.gov.
Issued in Kansas City, Missouri, on
October 3, 2008.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8–24136 Filed 10–9–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1082; Directorate
Identifier 2007–NM–337–AD]
sroberts on PROD1PC70 with PROPOSALS
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 Airplanes; Model A300 B4–601,
B4–603, B4–620, B4–622, B4–605R,
B4–622R, F4–605R, F4–622R, and C4–
605R Variant F Airplanes (Collectively
Called A300–600 Series Airplanes);
and Model A310 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
18:38 Oct 09, 2008
Jkt 217001
Notice of proposed rulemaking
(NPRM).
ACTION:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all of the
airplanes identified above. The existing
AD currently requires revising the FAAapproved maintenance program to
include a new airplane maintenance
manual task that specifies a detailed
inspection after each ram air turbine
(RAT) retraction. That existing AD also
currently requires, for certain airplanes,
a one-time inspection to detect breaks in
the bottom flange fitting of the RAT and
corrective actions, if necessary; for
certain airplanes, an adjustment of the
ejection jack; and, for certain other
airplanes, replacement of the aluminum
part with an improved steel part. This
proposed AD also would continue to
require certain actions for additional
airplanes and would revise the FAAapproved maintenance program to
include procedures for replacing the
RAT swivel coupling fork fitting with a
new steel part only. This proposed AD
results from a report that an additional
swivel coupling of the RAT yoke fitting
was found cracked while accomplishing
the requirements of the existing AD. We
are proposing this AD to prevent
misrigging of the ejection jack of the
RAT and to ensure removal of any RAT
yoke fitting made from aluminum
material. Such conditions could result
in a broken or cracked swivel coupling
and consequent failure of the RAT yoke
fitting, which could result in the loss of
RAT function and possible loss of
critical flight control systems in the
event of certain emergency situations.
DATES: We must receive comments on
this proposed AD by November 10,
2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
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• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–1082; Directorate Identifier
2007–NM–337–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
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Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Proposed Rules
substantive verbal contact we receive
about this proposed AD.
sroberts on PROD1PC70 with PROPOSALS
Discussion
On January 24, 2007, we issued AD
2007–03–09, amendment 39–14920 (72
FR 5157, February 5, 2007), for all
Airbus Model A300 airplanes; Model
A300 B4–601, B4–603, B4–620, B4–622,
B4–605R, B4–622R, F4–605R, F4–622R,
and C4–605R variant F airplanes
(collectively called A300–600 series
airplanes); and Model A310 airplanes.
That AD requires revising the FAAapproved maintenance program to
include a new airplane maintenance
manual task that specifies a detailed
inspection after each ram air turbine
(RAT) retraction. That AD also requires,
for certain airplanes, a one-time
inspection to detect breaks in the
bottom flange fitting of the RAT and
corrective actions, if necessary; for
certain airplanes, an adjustment of the
ejection jack; and, for certain other
airplanes, replacement of the aluminum
part with an improved steel part. That
AD resulted from a report indicating
that the swivel coupling of the RAT
yoke fitting was found broken (due to a
static overload as a result of the ejection
jack of the RAT being misrigged). We
issued that AD to prevent failure of the
RAT yoke fitting, which could result in
the loss of RAT function and possible
loss of critical flight control systems in
the event of certain emergency
situations.
Actions Since Existing AD Was Issued
Since we issued AD 2007–03–09,
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, informed us that an
additional swivel coupling of the RAT
yoke fitting was found cracked while
accomplishing the requirements of that
AD. Investigation revealed that the crack
was initiated by a stress-corrosion
phenomenon on the aluminum material.
Misrigging of the ejection jack of the
RAT or a RAT yoke fitting that is made
from aluminum material, if not
corrected, could result in a broken or
cracked swivel coupling and consequent
failure of the RAT yoke fitting. This
condition could result in the loss of
RAT function and possible loss of
critical flight control systems in the
event of certain emergency situations.
EASA has also informed us that
certain Model A310 and A300–600
series airplanes equipped with
Hamilton Sundstrand RATs have a RAT
yoke fitting made from aluminum
material. Therefore, those airplanes are
now subject to the same replacement
VerDate Aug<31>2005
18:38 Oct 09, 2008
Jkt 217001
requirements of AD 2007–03–09 as
those airplanes equipped with Dowty
Rotol RATs.
Relevant Service Information
Airbus has issued Service Bulletin
A310–57–2086, Revision 01, dated
September 3, 2007 (for Model A310
series airplanes); and Service Bulletin
A300–57–6099, Revision 01, dated
September 3, 2007 (for Model A300–600
series airplanes). (AD 2007–03–09 refers
to Airbus Service Bulletins A310–57–
2086, dated March 1, 2005, and A300–
57–6099, dated February 23, 2005; as
applicable; as appropriate sources of
service information for accomplishing
the required replacement.) The
replacement procedures specified in
Revision 01 of the service bulletins are
identical to that in the original issues of
the service bulletins. No additional
work is recommended for airplanes
modified by the original issues of the
service bulletins.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. EASA mandated the service
information and issued airworthiness
directive 2007–0273, dated October 23,
2007, to ensure the continued
airworthiness of these airplanes in the
European Union.
FAA’s Determination and Requirements
of the Proposed AD
These airplanes are manufactured in
France and are type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. As described
in FAA Order 8100.14A, ‘‘Interim
Procedures for Working with the
European Community on Airworthiness
Certification and Continued
Airworthiness,’’ dated August 12, 2005,
EASA has kept the FAA informed of the
situation described above. We have
examined EASA’s findings, evaluated
all pertinent information, and
determined that AD action is necessary
for airplanes of this type design that are
certificated for operation in the United
States.
This proposed AD would supersede
AD 2007–03–09. This proposed AD
would continue to require replacing the
aluminum yoke fitting of the swivel
coupling of the RAT with a new steel
yoke fitting and revising the FAAapproved maintenance program to
include a new airplane maintenance
manual task that specifies a detailed
inspection after each RAT retraction.
This proposed AD also would require
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Fmt 4702
Sfmt 4702
those actions for additional airplanes
and would revise the FAA-approved
maintenance program to include
procedures for replacing the RAT swivel
coupling fork fitting with a new steel
part only (the existing procedures allow
replacement with either an aluminum or
steel part).
Difference Between This AD and EASA
Airworthiness Directive
EASA airworthiness directive 2007–
0273 applies to the following U.S.registered airplanes: Airbus Model A310
and A300–600 series airplanes, except
for airplanes on which Airbus
Modification 12986 or 19578 has been
done in production or on which Airbus
Service Bulletin A310–57–2086 or
A300–57–6099 has been done. This
proposed AD, as did AD 2007–03–09,
would affect all Model A300, A300–600,
and A310 series airplanes. AD 2007–03–
09 combined two French airworthiness
directives (i.e., F–2005–089, dated June
8, 2005, and F–2005–090 R1, dated July
6, 2005), which affect additional
airplanes not identified in EASA
airworthiness directive 2007–0273.
Unlike EASA airworthiness directive
2007–0273, this proposed AD would
require revising the FAA-approved
maintenance program to specify an
inspection for breaks of the bottom
flange of the RAT swivel coupling yoke
fitting after each RAT retraction; and
replacement of the RAT swivel coupling
yoke fitting with a new steel part. This
action is necessary to ensure that only
steel yoke fittings are installed.
Change to Existing AD
This proposed AD would retain
certain requirements of AD 2007–03–09.
Since AD 2007–03–09 was issued, the
AD format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in
AD 2007–03–09
Corresponding
requirement in
this
proposed AD
Paragraph (b) ......................
Paragraph (c) ......................
Paragraph (f).
Paragraph (g).
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
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Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Proposed Rules
ESTIMATED COSTS
Action
Replacement ............................................
Revision of FAA-approved maintenance
program ................................................
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.
sroberts on PROD1PC70 with PROPOSALS
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
Jkt 217001
Number of
U.S.-registered
airplanes
Cost per
airplane
Fleet cost
$80
$470
$1,590
205
$325,950
1
Authority for This Rulemaking
18:38 Oct 09, 2008
Parts
14
In consideration of the compliance
time and effective date for
accomplishing the replacement and
revision of the FAA-approved
maintenance program required by AD
2007–03–09 (retained in paragraphs (f)
and (g) of this proposed AD), we assume
that operators of the affected airplanes
have already initiated the required
actions. The proposed AD would add no
new costs associated with those
airplanes.
VerDate Aug<31>2005
Average labor
rate per hour
Work hours
80
None
80
205
16,400
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. 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, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14920 (72
FR 5157, February 5, 2007) and adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2008–1082;
Directorate Identifier 2007–NM–337–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by November 10, 2008.
Affected ADs
(b) This AD supersedes AD 2007–03–09.
Applicability
(c) This AD applies to all Model A300
airplanes; Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F airplanes;
and Model A310 airplanes, certificated in
any category.
Unsafe Condition
(d) This AD results from a report that an
additional swivel coupling of the RAT yoke
fitting was found cracked while
accomplishing the requirements of the
existing AD. We are issuing this AD to
prevent misrigging of the ejection jack of the
ram air turbine (RAT) and to ensure removal
of any RAT yoke fitting made from aluminum
material. Such conditions could result in a
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Frm 00014
Fmt 4702
Sfmt 4702
broken or cracked swivel coupling and
consequent failure of the RAT yoke fitting,
which could result in the loss of RAT
function and possible loss of critical flight
control systems in the event of certain
emergency situations.
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.
Certain Requirements of AD 2007–03–09:
Replacement
(f) For Model A300 airplanes, Model
A300–600 series airplanes, and Model A310
airplanes equipped with Dowty Rotol RATs,
except airplanes on which Airbus
Modification 12986 has been done: Within 12
months after March 12, 2007 (the effective
date of AD 2007–03–09), replace the RAT
swivel coupling fork fitting with a new steel
fitting, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–0244, dated March
4, 2005 (for Model A300 airplanes); A300–
57–6099, dated February 23, 2005 (for Model
A300–600 series airplanes); or A310–57–
2086, dated March 1, 2005 (for Model A310
airplanes); as applicable; except as provided
by paragraph (h) of this AD.
Revisions of FAA-Approved Maintenance
Program
(g) For all airplanes: Within 3 months after
March 12, 2007, incorporate the information
in the applicable aircraft maintenance
manual (AMM) specified in paragraphs (g)(1),
(g)(2), and (g)(3) of this AD, into the FAAapproved maintenance program to specify an
inspection for breaks of the bottom flange of
the RAT swivel coupling yoke fitting after
each RAT retraction; and replacement of the
RAT swivel coupling yoke fitting with a new
aluminum or steel part as applicable; in
accordance with a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
´ ´
Direction Generale de l’Aviation Civile (or its
delegated agent); or European Aviation Safety
Agency (or its delegated agent). The page
blocks specified in paragraphs (g)(1), (g)(2),
and (g)(3) of this AD, as applicable, are one
approved method for the actions required by
paragraph (g) of this AD. Thereafter, except
as provided by paragraph (l) of this AD, no
alternative inspection intervals may be
approved for the bottom flange of the RAT
swivel coupling yoke fitting.
(1) Airbus A300–600 AMM, Chapter 29–
25–00, Page Block 301, dated June 1, 2005.
(2) Airbus A310 AMM, Chapter 29–25–00,
Page Block 301, dated June 1, 2005.
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Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Proposed Rules
(3) Airbus A300 AMM Chapter 29–25–00,
Page Block 301, dated March 1, 2006.
Note 1: After revising the maintenance
program to include the required periodic
inspections according to paragraph (g) or (k)
of this AD, operators do not need to make a
maintenance log entry to show compliance
with this AD every time those inspections are
accomplished thereafter.
the operator must request approval for an
alternative method of compliance according
to paragraph (l) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued damage tolerance of the affected
structure. The FAA has provided guidance
for this determination in Advisory Circular
(AC) 25–1529–1.
Note 2: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
New Requirements of This AD
Revised Service Bulletins
(h) As of the effective date of this AD, use
only the Accomplishment Instructions of
Airbus Service Bulletin A310–57–2086,
Revision 01, dated September 3, 2007 (for
Model A310 series airplanes); or Airbus
Service Bulletin A300–57–6099, Revision 01,
dated September 3, 2007 (for Model A300–
600 series airplanes); as applicable; to do the
replacement required by paragraph (f) of this
AD.
Replacement
(i) For airplanes identified in Table 1 of
this AD: Before 102 months since first flight,
or within 12 months after the effective date
of this AD, whichever occurs later, replace
the aluminum yoke fitting of the swivel
coupling of the RAT with a new steel yoke
fitting, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–57–2086, Revision 01,
dated September 3, 2007 (for Model A310
series airplanes); or Airbus Service Bulletin
A300–57–6099, Revision 01, dated
September 3, 2007 (for Model A300–600
series airplanes); as applicable.
TABLE 1—APPLICABILITY OF PARAGRAPH (I) OF THIS AD
Model—
Except for those airplanes on which—
(1) A310 series airplanes equipped with Hamilton Sundstrand RAT.
Airbus Modification 12986 or 19578 has been
done in production.
(2) A300–600 series airplanes equipped with
Hamilton Sundstrand RAT.
Airbus Modification 12986 or 19578 has been
done in production.
(j) Replacements done before the effective
date of this AD in accordance with Airbus
Service Bulletin A310–57–2086, dated March
1, 2005 (for Model A310 series airplanes); or
Airbus Service Bulletin A300–57–6099,
dated February 23, 2005 (for Model A300–
600 series airplane); as applicable; are
acceptable for compliance with the
requirements of paragraph (i) of this AD.
sroberts on PROD1PC70 with PROPOSALS
Revision of FAA-Approved Maintenance
Program
(k) For all airplanes: Within 3 months after
the effective date of this AD, incorporate the
information in the applicable AMM specified
in paragraphs (k)(1), (k)(2), and (k)(3) of this
AD, into the FAA-approved maintenance
program to specify an inspection for breaks
of the bottom flange of the RAT swivel
coupling yoke fitting after each RAT
retraction; and replacement of the RAT
swivel coupling yoke fitting with a new steel
part; in accordance with a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
European Aviation Safety Agency (or its
delegated agent). The page blocks specified
in paragraphs (k)(1), (k)(2), and (k)(3) of this
AD, as applicable, that contain the inspection
and replacement described previously are
one approved method for the actions
required by paragraph (k) of this AD.
Thereafter, except as provided by paragraph
(l) of this AD, no alternative inspection
intervals may be approved for the bottom
flange of the RAT swivel coupling yoke
fitting. Accomplishing this incorporation
terminates the requirements of paragraph (g)
of this AD.
(1) Airbus A300–600 AMM, Chapter 29–
25–00, Page Block 301.
VerDate Aug<31>2005
18:38 Oct 09, 2008
Jkt 217001
Or on which—
Airbus Service Bulletin A310–57–2086, dated
March 1, 2005; or Revision 01, dated September 3, 2007 has been done in service.
Airbus Service Bulletin A300–57–6099, dated
February 23, 2005; or Revision 01, dated
September 3, 2007; has been done in service.
(2) Airbus A310 AMM, Chapter 29–25–00,
Page Block 301.
(3) Airbus A300 AMM Chapter 29–25–00,
Page Block 301.
DEPARTMENT OF TRANSPORTATION
Alternative Methods of Compliance
(AMOCs)
14 CFR Part 39
(l) 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: Vladimir Ulyanov,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone (425)
227–1138; fax (425) 227–1149. 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.
[Docket No. FAA–2008–1083; Directorate
Identifier 2008–NM–130–AD]
Related Information
(m) European Aviation Safety Agency
(EASA) airworthiness directive 2007–0273,
dated October 23, 2007, and French
airworthiness directive F–2005–089, dated
June 8, 2005, also address the subject of this
AD.
Issued in Renton, Washington, on October
2, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–24151 Filed 10–9–08; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
Notice of proposed rulemaking
(NPRM).
ACTION:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
There have been several cases reported
where the landing gear did not retract after
take-off. Subsequent investigation revealed
this was caused by fatigue failure of the nose
landing gear electrical harness. In
conjunction with one engine being
inoperable, this could, in certain operating
conditions, affect continued safe flight and
landing.
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Agencies
[Federal Register Volume 73, Number 198 (Friday, October 10, 2008)]
[Proposed Rules]
[Pages 60203-60206]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-24151]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1082; Directorate Identifier 2007-NM-337-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Airplanes; Model A300
B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and
C4-605R Variant F Airplanes (Collectively Called A300-600 Series
Airplanes); and Model A310 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all of the airplanes identified above.
The existing AD currently requires revising the FAA-approved
maintenance program to include a new airplane maintenance manual task
that specifies a detailed inspection after each ram air turbine (RAT)
retraction. That existing AD also currently requires, for certain
airplanes, a one-time inspection to detect breaks in the bottom flange
fitting of the RAT and corrective actions, if necessary; for certain
airplanes, an adjustment of the ejection jack; and, for certain other
airplanes, replacement of the aluminum part with an improved steel
part. This proposed AD also would continue to require certain actions
for additional airplanes and would revise the FAA-approved maintenance
program to include procedures for replacing the RAT swivel coupling
fork fitting with a new steel part only. This proposed AD results from
a report that an additional swivel coupling of the RAT yoke fitting was
found cracked while accomplishing the requirements of the existing AD.
We are proposing this AD to prevent misrigging of the ejection jack of
the RAT and to ensure removal of any RAT yoke fitting made from
aluminum material. Such conditions could result in a broken or cracked
swivel coupling and consequent failure of the RAT yoke fitting, which
could result in the loss of RAT function and possible loss of critical
flight control systems in the event of certain emergency situations.
DATES: We must receive comments on this proposed AD by November 10,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-1082;
Directorate Identifier 2007-NM-337-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each
[[Page 60204]]
substantive verbal contact we receive about this proposed AD.
Discussion
On January 24, 2007, we issued AD 2007-03-09, amendment 39-14920
(72 FR 5157, February 5, 2007), for all Airbus Model A300 airplanes;
Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R,
F4-622R, and C4-605R variant F airplanes (collectively called A300-600
series airplanes); and Model A310 airplanes. That AD requires revising
the FAA-approved maintenance program to include a new airplane
maintenance manual task that specifies a detailed inspection after each
ram air turbine (RAT) retraction. That AD also requires, for certain
airplanes, a one-time inspection to detect breaks in the bottom flange
fitting of the RAT and corrective actions, if necessary; for certain
airplanes, an adjustment of the ejection jack; and, for certain other
airplanes, replacement of the aluminum part with an improved steel
part. That AD resulted from a report indicating that the swivel
coupling of the RAT yoke fitting was found broken (due to a static
overload as a result of the ejection jack of the RAT being misrigged).
We issued that AD to prevent failure of the RAT yoke fitting, which
could result in the loss of RAT function and possible loss of critical
flight control systems in the event of certain emergency situations.
Actions Since Existing AD Was Issued
Since we issued AD 2007-03-09, European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, informed us that an additional swivel coupling of
the RAT yoke fitting was found cracked while accomplishing the
requirements of that AD. Investigation revealed that the crack was
initiated by a stress-corrosion phenomenon on the aluminum material.
Misrigging of the ejection jack of the RAT or a RAT yoke fitting
that is made from aluminum material, if not corrected, could result in
a broken or cracked swivel coupling and consequent failure of the RAT
yoke fitting. This condition could result in the loss of RAT function
and possible loss of critical flight control systems in the event of
certain emergency situations.
EASA has also informed us that certain Model A310 and A300-600
series airplanes equipped with Hamilton Sundstrand RATs have a RAT yoke
fitting made from aluminum material. Therefore, those airplanes are now
subject to the same replacement requirements of AD 2007-03-09 as those
airplanes equipped with Dowty Rotol RATs.
Relevant Service Information
Airbus has issued Service Bulletin A310-57-2086, Revision 01, dated
September 3, 2007 (for Model A310 series airplanes); and Service
Bulletin A300-57-6099, Revision 01, dated September 3, 2007 (for Model
A300-600 series airplanes). (AD 2007-03-09 refers to Airbus Service
Bulletins A310-57-2086, dated March 1, 2005, and A300-57-6099, dated
February 23, 2005; as applicable; as appropriate sources of service
information for accomplishing the required replacement.) The
replacement procedures specified in Revision 01 of the service
bulletins are identical to that in the original issues of the service
bulletins. No additional work is recommended for airplanes modified by
the original issues of the service bulletins.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. EASA mandated the
service information and issued airworthiness directive 2007-0273, dated
October 23, 2007, to ensure the continued airworthiness of these
airplanes in the European Union.
FAA's Determination and Requirements of the Proposed AD
These airplanes are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, EASA has kept the FAA informed of the situation
described above. We have examined EASA's findings, evaluated all
pertinent information, and determined that AD action is necessary for
airplanes of this type design that are certificated for operation in
the United States.
This proposed AD would supersede AD 2007-03-09. This proposed AD
would continue to require replacing the aluminum yoke fitting of the
swivel coupling of the RAT with a new steel yoke fitting and revising
the FAA-approved maintenance program to include a new airplane
maintenance manual task that specifies a detailed inspection after each
RAT retraction. This proposed AD also would require those actions for
additional airplanes and would revise the FAA-approved maintenance
program to include procedures for replacing the RAT swivel coupling
fork fitting with a new steel part only (the existing procedures allow
replacement with either an aluminum or steel part).
Difference Between This AD and EASA Airworthiness Directive
EASA airworthiness directive 2007-0273 applies to the following
U.S.-registered airplanes: Airbus Model A310 and A300-600 series
airplanes, except for airplanes on which Airbus Modification 12986 or
19578 has been done in production or on which Airbus Service Bulletin
A310-57-2086 or A300-57-6099 has been done. This proposed AD, as did AD
2007-03-09, would affect all Model A300, A300-600, and A310 series
airplanes. AD 2007-03-09 combined two French airworthiness directives
(i.e., F-2005-089, dated June 8, 2005, and F-2005-090 R1, dated July 6,
2005), which affect additional airplanes not identified in EASA
airworthiness directive 2007-0273.
Unlike EASA airworthiness directive 2007-0273, this proposed AD
would require revising the FAA-approved maintenance program to specify
an inspection for breaks of the bottom flange of the RAT swivel
coupling yoke fitting after each RAT retraction; and replacement of the
RAT swivel coupling yoke fitting with a new steel part. This action is
necessary to ensure that only steel yoke fittings are installed.
Change to Existing AD
This proposed AD would retain certain requirements of AD 2007-03-
09. Since AD 2007-03-09 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2007-03-09 this proposed AD
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Paragraph (b)........................... Paragraph (f).
Paragraph (c)........................... Paragraph (g).
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Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
[[Page 60205]]
Estimated Costs
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Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
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Replacement............................................. 14 $80 $470 $1,590 205 $325,950
Revision of FAA-approved maintenance program............ 1 80 None 80 205 16,400
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In consideration of the compliance time and effective date for
accomplishing the replacement and revision of the FAA-approved
maintenance program required by AD 2007-03-09 (retained in paragraphs
(f) and (g) of this proposed AD), we assume that operators of the
affected airplanes have already initiated the required actions. The
proposed AD would add no new costs associated with those airplanes.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14920 (72 FR 5157, February 5, 2007) and adding
the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2008-1082; Directorate Identifier 2007-NM-
337-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
10, 2008.
Affected ADs
(b) This AD supersedes AD 2007-03-09.
Applicability
(c) This AD applies to all Model A300 airplanes; Model A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and
C4-605R Variant F airplanes; and Model A310 airplanes, certificated
in any category.
Unsafe Condition
(d) This AD results from a report that an additional swivel
coupling of the RAT yoke fitting was found cracked while
accomplishing the requirements of the existing AD. We are issuing
this AD to prevent misrigging of the ejection jack of the ram air
turbine (RAT) and to ensure removal of any RAT yoke fitting made
from aluminum material. Such conditions could result in a broken or
cracked swivel coupling and consequent failure of the RAT yoke
fitting, which could result in the loss of RAT function and possible
loss of critical flight control systems in the event of certain
emergency situations.
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.
Certain Requirements of AD 2007-03-09:
Replacement
(f) For Model A300 airplanes, Model A300-600 series airplanes,
and Model A310 airplanes equipped with Dowty Rotol RATs, except
airplanes on which Airbus Modification 12986 has been done: Within
12 months after March 12, 2007 (the effective date of AD 2007-03-
09), replace the RAT swivel coupling fork fitting with a new steel
fitting, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-0244, dated March 4, 2005 (for Model
A300 airplanes); A300-57-6099, dated February 23, 2005 (for Model
A300-600 series airplanes); or A310-57-2086, dated March 1, 2005
(for Model A310 airplanes); as applicable; except as provided by
paragraph (h) of this AD.
Revisions of FAA-Approved Maintenance Program
(g) For all airplanes: Within 3 months after March 12, 2007,
incorporate the information in the applicable aircraft maintenance
manual (AMM) specified in paragraphs (g)(1), (g)(2), and (g)(3) of
this AD, into the FAA-approved maintenance program to specify an
inspection for breaks of the bottom flange of the RAT swivel
coupling yoke fitting after each RAT retraction; and replacement of
the RAT swivel coupling yoke fitting with a new aluminum or steel
part as applicable; in accordance with a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the Direction G[eacute]n[eacute]rale de
l'Aviation Civile (or its delegated agent); or European Aviation
Safety Agency (or its delegated agent). The page blocks specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD, as applicable, are
one approved method for the actions required by paragraph (g) of
this AD. Thereafter, except as provided by paragraph (l) of this AD,
no alternative inspection intervals may be approved for the bottom
flange of the RAT swivel coupling yoke fitting.
(1) Airbus A300-600 AMM, Chapter 29-25-00, Page Block 301, dated
June 1, 2005.
(2) Airbus A310 AMM, Chapter 29-25-00, Page Block 301, dated
June 1, 2005.
[[Page 60206]]
(3) Airbus A300 AMM Chapter 29-25-00, Page Block 301, dated
March 1, 2006.
Note 1: After revising the maintenance program to include the
required periodic inspections according to paragraph (g) or (k) of
this AD, operators do not need to make a maintenance log entry to
show compliance with this AD every time those inspections are
accomplished thereafter.
Note 2: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (l) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued damage tolerance of the affected structure. The FAA
has provided guidance for this determination in Advisory Circular
(AC) 25-1529-1.
New Requirements of This AD
Revised Service Bulletins
(h) As of the effective date of this AD, use only the
Accomplishment Instructions of Airbus Service Bulletin A310-57-2086,
Revision 01, dated September 3, 2007 (for Model A310 series
airplanes); or Airbus Service Bulletin A300-57-6099, Revision 01,
dated September 3, 2007 (for Model A300-600 series airplanes); as
applicable; to do the replacement required by paragraph (f) of this
AD.
Replacement
(i) For airplanes identified in Table 1 of this AD: Before 102
months since first flight, or within 12 months after the effective
date of this AD, whichever occurs later, replace the aluminum yoke
fitting of the swivel coupling of the RAT with a new steel yoke
fitting, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A310-57-2086, Revision 01, dated September
3, 2007 (for Model A310 series airplanes); or Airbus Service
Bulletin A300-57-6099, Revision 01, dated September 3, 2007 (for
Model A300-600 series airplanes); as applicable.
Table 1--Applicability of paragraph (i) of This AD
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Except for those
Model-- airplanes on which-- Or on which--
------------------------------------------------------------------------
(1) A310 series airplanes Airbus Modification Airbus Service
equipped with Hamilton 12986 or 19578 has Bulletin A310-57-
Sundstrand RAT. been done in 2086, dated March
production. 1, 2005; or
Revision 01, dated
September 3, 2007
has been done in
service.
(2) A300-600 series Airbus Modification Airbus Service
airplanes equipped with 12986 or 19578 has Bulletin A300-57-
Hamilton Sundstrand RAT. been done in 6099, dated
production. February 23, 2005;
or Revision 01,
dated September 3,
2007; has been done
in service.
------------------------------------------------------------------------
(j) Replacements done before the effective date of this AD in
accordance with Airbus Service Bulletin A310-57-2086, dated March 1,
2005 (for Model A310 series airplanes); or Airbus Service Bulletin
A300-57-6099, dated February 23, 2005 (for Model A300-600 series
airplane); as applicable; are acceptable for compliance with the
requirements of paragraph (i) of this AD.
Revision of FAA-Approved Maintenance Program
(k) For all airplanes: Within 3 months after the effective date
of this AD, incorporate the information in the applicable AMM
specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD, into
the FAA-approved maintenance program to specify an inspection for
breaks of the bottom flange of the RAT swivel coupling yoke fitting
after each RAT retraction; and replacement of the RAT swivel
coupling yoke fitting with a new steel part; in accordance with a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or European Aviation Safety
Agency (or its delegated agent). The page blocks specified in
paragraphs (k)(1), (k)(2), and (k)(3) of this AD, as applicable,
that contain the inspection and replacement described previously are
one approved method for the actions required by paragraph (k) of
this AD. Thereafter, except as provided by paragraph (l) of this AD,
no alternative inspection intervals may be approved for the bottom
flange of the RAT swivel coupling yoke fitting. Accomplishing this
incorporation terminates the requirements of paragraph (g) of this
AD.
(1) Airbus A300-600 AMM, Chapter 29-25-00, Page Block 301.
(2) Airbus A310 AMM, Chapter 29-25-00, Page Block 301.
(3) Airbus A300 AMM Chapter 29-25-00, Page Block 301.
Alternative Methods of Compliance (AMOCs)
(l) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149.
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
(m) European Aviation Safety Agency (EASA) airworthiness
directive 2007-0273, dated October 23, 2007, and French
airworthiness directive F-2005-089, dated June 8, 2005, also address
the subject of this AD.
Issued in Renton, Washington, on October 2, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-24151 Filed 10-9-08; 8:45 am]
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