[Federal Register: December 24, 2002 (Volume 67, Number 247)]
[Proposed Rules]
[Page 78394-78397]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24de02-25]
[[Page 78394]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-CE-49-AD]
RIN 2120-AA64
Airworthiness Directives; Socata--Groupe Aerospatiale Models MS
892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 150T,
and Rallye 150ST Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede Airworthiness Directive
(AD) 2002-05-04, which applies to certain Socata Models MS 892A-150, MS
892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 150T, and Rallye
150ST airplanes. AD 2002-05-04 requires you to repetitively inspect any
engine mount assembly that is not part number 892-51-0-035-0 (or FAA-
approved equivalent part number) for cracks; repair cracks that do not
exceed a certain length; and replace the engine mount when the cracks
exceed a certain length and cracks are found on an engine mount that
already has been repaired twice. This proposed AD is the result of the
French airworthiness authority's determination that airplanes equipped
with an engine mount assembly part number 892-51-0-035-0 also display
the unsafe condition. This proposed AD would retain the repetitive
inspection and repair requirements of AD 2002-05-04, change the
applicability section, remove the terminating action, and require
replacement of all part number 892-51-0-035-0 engine mount assemblies.
The actions specified by this proposed AD are intended to prevent
failure of the engine mount assembly. Such failure could result in loss
of control of the airplane.
DATES: The Federal Aviation Administration (FAA) must receive any
comments on this rule on or before January 31, 2003.
ADDRESSES: Submit comments to FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2002-CE-49-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. You may view any
comments at this location between 8 a.m. and 4 p.m., Monday through
Friday, except Federal holidays. You may also send comments
electronically to the following address: 9-ACE-7-Docket@faa.gov.
Comments sent electronically must contain ``Docket No. 2002-CE-49-AD''
in the subject line. If you send comments electronically as attached
electronic files, the files must be formatted in Microsoft Word 97 for
Windows or ASCII text.
You may get service information that applies to this proposed AD
from Socata Groupe Aerospatiale, Customer Support, Aerodrome Tarbes-
Ossun-Lourdes, BP 930-F65009 Tarbes Cedex, France; telephone: 011 33 5
62 41 73 00; facsimile: 011 33 5 62 41 76 54; or the Product Support
Manager, Socata--Groupe Aerospatiale, North Perry Airport, 7501
Pembroke Road, Pembroke Pines, Florida 33023; telephone: (954) 894-
1160; facsimile: (954) 964-4141. You may also view this information at
the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4146; facsimile: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
How Do I Comment on This Proposed AD?
The FAA invites comments on this proposed rule. You may submit
whatever written data, views, or arguments you choose. You need to
include the rule's docket number and submit your comments to the
address specified under the caption ADDRESSES. We will consider all
comments received on or before the closing date. We may amend this
proposed rule in light of comments received. Factual information that
supports your ideas and suggestions is extremely helpful in evaluating
the effectiveness of this proposed AD action and determining whether we
need to take additional rulemaking action.
Are There Any Specific Portions of This Proposed AD I Should Pay
Attention to?
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed rule that
might suggest a need to modify this proposed rule. You may view all
comments we receive before and after the closing date of this proposed
rule in the Rules Docket. We will file a report in the Rules Docket
that summarizes each contact we have with the public that concerns the
substantive parts of this proposed AD.
How Can I Be Sure FAA Receives My Comment?
If you want FAA to acknowledge the receipt of your mailed comments,
you must include a self-addressed, stamped postcard. On the postcard,
write ``Comments to Docket No. 2002-CE-49-AD.'' We will date stamp and
mail the postcard back to you.
Discussion
Has FAA Taken Any Action to This Point?
Fatigue cracks found on the engine mount assemblies of certain
Socata Models MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS
894E, Rallye 150T, and Rallye 150ST airplanes caused us to issue AD
2002-05-04, Amendment 39-12672 (67 FR 10831, March 11, 2002). This AD
requires the following on affected airplane models and serial numbers
that are certificated in any category and do not have a part number
892-51-0-035-0 engine mount assembly (or FAA-approved equivalent part
number) installed:
--Repetitively inspecting any engine mount assembly that is not part
number 892-51-0-035-0 (or FAA-approved equivalent part number) for
cracks;
--Repairing cracks that do not exceed a certain length;
--Replacing the engine mount when the cracks exceed a certain length
and cracks are found on an engine mount that already has two repairs;
and
--Terminating repetitive inspections after installing a part number
892-51-0-035-0 engine mount assembly, (or FAA-approved equivalent part
number).
AD 2002-05-04 superseded AD 77-15-06, Amendment 39-2975, which
required accomplishing the following:
--Inspecting the engine mount assembly for cracks at repetitive
intervals;
--Repairing any cracks found; and
--Modifying the brackets on airplanes with right angle engine mounts.
AD 2002-05-04 incorporated new manufacturer service information to
address the unsafe condition, added additional airplane models to the
applicability; and changed the initial compliance time for all
airplanes.
Accomplishment of these actions is required in accordance with
Socata Service Bulletin SB 156-71, dated May 2001.
What Has Happened Since AD 2002-05-04 To Initiate This Action?
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the
[[Page 78395]]
airworthiness authority for France, recently notified FAA of the need
to change AD 2002-05-04. The DGAC reports that affected airplanes
equipped with an engine mount assembly part number 892-51-0-035-0 are
also affected by fatigue cracking and should be included in the
applicability section of AD 2002-05-04. Installing part number 892-51-
0-035-0 is no longer considered a terminating action for the repetitive
inspections and should be removed from all affected airplanes.
What Action Did the DGAC Take?
The DGAC classified Socata Service Bulletin SB 156-71, dated May
2001, as mandatory and issued French AD 2001-400(A), dated September
19, 2001; and French AD 1978-205(A) R1, dated September 19, 2001; in
order to ensure the continued airworthiness of these airplanes in
France.
Was This in Accordance With the Bilateral Airworthiness Agreement?
These airplane models 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.
Pursuant to this bilateral airworthiness agreement, DGAC has kept
FAA informed of the situation described above.
The FAA's Determination and an Explanation of the Provisions of This
Proposed AD
What Has FAA Decided?
The FAA has examined the findings of the DGAC; reviewed all
available information, including the service information referenced
above; and determined that:
--The unsafe condition referenced in this document exists or could
develop on certain Socata Models MS 892A-150, MS 892E-150, MS 893A, MS
893E, MS 894A, MS 894E, Rallye 150T, and Rallye 150ST airplanes of the
same type design that are on the U.S. registry;
--The inspection and repair actions specified in AD 2002-05-04 should
be accomplished on certain affected airplanes; and
--AD action should be taken in order to correct this unsafe condition.
What Would This Proposed AD Require?
This proposed AD would supersede AD 2002-05-04 with a new AD that
would:
--Retain the repetitive inspection and repair requirements of AD 2002-
05-04;
--Remove the terminating action;
--Change the applicability section; and
--Require replacement of all part number 892-51-0-035-0 engine mount
assemblies with an FAA-approved equivalent part number.
Cost Impact
How Many Airplanes Would This Proposed AD Impact?
We estimate that this proposed AD affects 81 airplanes in the U.S.
registry.
What Would Be the Cost Impact of This Proposed AD on Owners/Operators
of the Affected Airplanes?
We estimate the following costs to accomplish each proposed
inspection(s):
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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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1 workhour x $60 = $60............ No parts required... $60 $60 x 81 = $4,860
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We estimate the following costs to accomplish any necessary repairs
that would be required based on the results of the proposed
inspection(s). We have no way of determining the number of airplanes
that may need such repair:
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Total cost per
Labor cost Parts cost airplane
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3 workhours x $60 = $180....... No parts required..... $180
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We estimate the following costs to accomplish the proposed
replacement. We have no way of determining the number of airplanes that
may need such replacement:
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Labor cost Parts cost Total cost per airplane
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20 workhours x $60 = $1,200............ Approximately $3,360...... $1,200 + $3,360 = $4,560
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What Is the Difference Between the Cost Impact of This Proposed AD and
the Cost Impact of AD 2002-05-04?
The differences between this proposed AD and AD 2002-05-04 are the
correction to the applicability section, removal of the terminating
action, and the addition of replacing all part number 892-51-0-035-0
engine mount assemblies. We have determined that this proposed AD
action does increase the cost impact over that already required by AD
2002-05-04.
Regulatory Impact
Would This Proposed AD Impact Various Entities?
The regulations proposed herein 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. Therefore, it
is determined that this proposed rule would not have federalism
implications under Executive Order 13132.
Would This Proposed AD Involve a Significant Rule or Regulatory Action?
For the reasons discussed above, I certify that this action (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) if promulgated,
will not have a significant
[[Page 78396]]
economic impact, positive or negative, on a substantial number of small
entities under the criteria of the Regulatory Flexibility Act. A copy
of the draft regulatory evaluation prepared for this action has been
placed in the Rules Docket. A copy of it may be obtained by contacting
the Rules Docket at the location provided under the caption ADDRESSES.
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 Federal Aviation Administration proposes to amend 14
CFR part 39 of the Federal Aviation Regulations 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. FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2002-05-04, Amendment 39-12672 (67 FR 10831, March 11, 2002), and by
adding a new AD to read as follows:
Socata--Groupe Aerospatiale: Docket No. 2002-CE-49-AD; Supersedes AD
2002-05-04, Amendment 39-12672.
(a) What airplanes are affected by this AD? This AD affects the
following airplane models and serial numbers that are certificated
in any category:
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Model Serial Nos.
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MS 892A-150........................... All serial numbers.
MS 892E-150........................... All serial numbers.
MS 893A............................... All serial numbers.
MS 893E............................... All serial numbers.
MS 894A............................... 1005 through 2204 equipped with
kit OPT8098 9037.
MS 894E............................... 1005 through 2204 equipped with
kit OPT8098 9037.
Rallye 150T........................... All serial numbers.
Rallye 150ST.......................... All serial numbers.
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(b) Who must comply with this AD? Anyone who wishes to operate
any of airplanes identified in paragraph (a) of this AD must comply
with this AD.
(c) What problem does this AD address? The actions specified by
this AD are intended to detect and correct cracks in the engine
mount assembly. Such a condition could cause the engine mount
assembly to fail, which could result in loss of control of the
airplane.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
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Actions Compliance Procedures
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(1) Replace any part number 892- Within the next 50 In accordance with
51-0-035-0 engine mount hours time-in- the applicable
assembly with an FAA-approved service (TIS) maintenance
assembly that is not part after the manual.
number 892-51-0-035-0. effective date of
this AD.
(2) Inspect the engine mount Initially inspect In accordance with
assembly for cracks. at whichever of the
the following Accomplishment
occurs later: Instructions
after section of Socata
accumulating 50 Service Bulletin
hours TIS after SB 156-71, dated
engine mount May 2001.
assembly
installation;
within the next
20 hours TIS
after the
effective date of
this AD; or at
the next
inspection
required by AD
2002-05-04.
Repetitively
inspect
thereafter at
intervals not to
exceed 50 hours
TIS.
(3) If any crack is found during Prior to further In accordance with
any inspection required by flight after the the
paragraph (d)(2) of this AD inspection in Accomplishment
that is less than 0.24 inches which the crack Instructions
(6 mm) in length, repair the is found. section of Socata
engine mount assembly. If two Service Bulletin
repairs on the engine mount SB 156-71, dated
have already been performed, May 2001.
repair in accordance with
paragraph (d)(4) of this AD.
(4) If any crack is found during Prior to further In accordance with
any inspection required by this flight after the the repair scheme
AD that is 0.24 inches (6 mm) inspection in obtained from
or longer in length, or if any which the crack Socata Groupe
crack is found and two repairs is found. Aerospatiale,
on the engine mount have Customer Support,
already been performed:. Aerodrome Tarbes-
(i) Obtain a repair scheme from Ossun-Lourdes, BP
the manufacturer through the 930-F65009 Tarbes
FAA at the address specified in Cedex, France; or
paragraph (g) of this AD; and. the Product
(ii) Incorporate this repair Support Manager,
scheme.. Socata--Groupe
Aerospatiale,
North Perry
Airport, 7501
Pembroke Road,
Pembroke Pines,
Florida 33023.
Obtain this
repair scheme
through the FAA
at the address
specified in
paragraph (f) of
this AD.
(5) Do not install on any As of the Not applicable.
airplane engine mount assembly effective date of
part number 892-51-0-035-0. this AD.
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(e) Can I comply with this AD in any other way?
(1) You may use an alternative method of compliance or adjust
the compliance time if:
(i) Your alternative method of compliance provides an equivalent
level of safety; and
(ii) The Manager, Standards Office, Small Airplane Directorate,
approves your alternative. Submit your request through an FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Standards Office.
(2) Alternative methods of compliance approved in accordance
with AD 2002-05-04, which is superseded by this AD, are not approved
as alternative methods of compliance with this AD.
Note 1: This AD applies to each airplane identified in paragraph
(a) of this AD, regardless of whether it has been modified, altered,
or repaired in the area subject to the requirements of this AD. For
airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the owner/
operator must request approval for an alternative method of
compliance in accordance with paragraph (e) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD;
and, if you have not eliminated the unsafe condition, specific
actions you propose to address it.
[[Page 78397]]
(f) Where can I get information about any already-approved
alternative methods of compliance? Contact Karl Schletzbaum,
Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146;
facsimile: (816) 329-4090.
(g) What if I need to fly the airplane to another location to
comply with this AD? The FAA can issue a special flight permit under
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate your airplane to a location where
you can accomplish the requirements of this AD.
(h) How do I get copies of the documents referenced in this AD?
You may obtain copies of the documents referenced in this AD from
Socata Groupe Aerospatiale, Customer Support, Aerodrome Tarbes-
Ossun-Lourdes, BP 930--F65009 Tarbes Cedex, France; telephone: 011
33 5 62 41 73 00; facsimile: 011 33 5 62 41 76 54; or the Product
Support Manager, Socata--Groupe Aerospatiale, North Perry Airport,
7501 Pembroke Road, Pembroke Pines, Florida 33023; telephone: (954)
894-1160; facsimile: (954) 964-4141. You may examine these documents
at FAA, Central Region, Office of the Regional Counsel, 901 Locust,
Room 506, Kansas City, Missouri 64106.
(i) Does this AD action affect any existing AD actions? This
amendment supersedes AD 2002-05-04, Amendment 39-12672.
Note 2: The subject of this AD is addressed in French AD 2001-
400(A), dated September 19, 2001; and French AD 1978-205(A) R1,
dated September 19, 2001.
Issued in Kansas City, Missouri, on December 17, 2002.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-32336 Filed 12-23-02; 8:45 am]
BILLING CODE 4910-13-P