[Federal Register Volume 66, Number 242 (Monday, December 17, 2001)]
[Proposed Rules]
[Pages 64928-64931]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-30953]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-41-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) 77-15-06, which applies to all SOCATA--Groupe Aerospatiale 
(Socata) Models MS 892A-150, MS 892E-150, MS 893A, MS 893E, Rallye 
150T, and Rallye 150ST airplanes. AD 77-15-06 currently requires you to 
repetitively inspect the engine mount assembly for cracks, repair any 
cracks found, and modify the brackets on airplanes with right angle 
engine mounts. This proposed AD is the result of the French 
airworthiness authority's determination that updated service 
information and additional aircraft should be added to the 
applicability of AD 77-15-06. This proposed AD would retain the 
inspection and repair requirements of the current AD and would add the 
information communicated by the French airworthiness authority. The 
actions specified by this proposed 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.

DATES: The Federal Aviation Administration (FAA) must receive any 
comments on this rule on or before January 11, 2002.

ADDRESSES: Submit comments to FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2001-CE-41-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 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) 964-4191. 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 the rule. You may 
view all comments we receive before and after the closing date of the 
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 comments, you must include a self-
addressed, stamped postcard. On the postcard, write ``Comments to 
Docket No. 2001-CE-41-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 Socata Models MS 892A-150, MS 892E-150, MS 
893A, MS 893E, Rallye 150T, and Rallye 150ST airplanes caused us to 
issue AD 77-15-06, Amendment 39-2975. This AD currently requires the 
following:

--Inspecting the engine mount assembly for cracks at repetitive 
intervals;

[[Page 64929]]

--Repairing any cracks found; and
--Modifying the brackets on airplanes with right angle engine mounts.
    What has happened since AD 77-15-06 to initiate this action? The 
Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, recently notified FAA of the need 
to change AD 77-15-06. The DGAC reports that:

--The manufacturer has issued new service information to address the 
unsafe condition;
--Additional airplane models should be added to the applicability; and
--The initial compliance time should be changed from 100 hours time-in-
service (TIS) to 50 hours TIS.

    Is there service information that applies to this subject? Socata 
has issued Service Bulletin SB 156-17, dated May 2001.
    What are the provisions of this service bulletin? The service 
bulletin includes procedures for:

--Repetitively inspecting certain engine mount assemblies for cracks; 
and
--Repairing cracks that are a certain length.

    What action did the DGAC take? The DGAC classified this service 
bulletin as mandatory and issued French AD 2001-400(A), 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 the 
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 actions specified in the previously-referenced service 
information should be accomplished on the affected airplanes; and
--AD action should be taken in order to correct this unsafe condition.

    What would the proposed AD require? This proposed AD would 
supersede AD 77-15-06 with a new AD that would require 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 two repairs.

Cost Impact

    How many airplanes would the proposed AD impact? We estimate that 
the 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):

----------------------------------------------------------------------------------------------------------------
                                                                     Total
              Labor cost                        Parts cost          cost per     Total cost on U.S. operators
                                                                    airplane
----------------------------------------------------------------------------------------------------------------
1 workhour  x  $60=$60................  No parts required........        $60  $60  x  81=$4,860
----------------------------------------------------------------------------------------------------------------

    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:

----------------------------------------------------------------------------------------------------------------
              Labor cost                         Parts cost                     Total cost per airplane
----------------------------------------------------------------------------------------------------------------
3 workhours  x  $60=$180.............  No parts required............  $180
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    We estimate the following costs to accomplish any necessary 
replacements 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 replacement:

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                 Labor cost                   Parts cost                  Total cost per airplane
----------------------------------------------------------------------------------------------------------------
9 workhours  x  $60=$540...................       $3,500  $540 + $3,500=$4,040
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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 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

[[Page 64930]]

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 Section 39.13 by removing Airworthiness Directive 
(AD) 77-15-06, Amendment 39-2975, and by adding a new AD to read as 
follows:

SOCATA--Groupe Aerospatiale: Docket No. 2001-CE-41-AD; Supersedes AD 
77-15-06, Amendment 39-2975.

    (a) What airplanes are affected by this AD? This AD affects the 
following 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:

------------------------------------------------------------------------
                Model                             Serial Nos.
------------------------------------------------------------------------
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.
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the above airplanes 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:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Inspect the engine mount      For airplanes       In accordance with
 assembly for cracks.              previously          the
                                   affected by AD 77-  Accomplishment
                                   15-06: inspect or   Instructions
                                   within the next     section of Socata
                                   50 hours time-in-   Service Bulletin
                                   service (TIS)       SB 156-71, dated
                                   after the last      May 2001.
                                   inspection
                                   required by AD 77-
                                   15-06 or within
                                   the next 50 hours
                                   TIS after the
                                   effective date of
                                   this AD,
                                   whichever occurs
                                   first, and
                                   thereafter at
                                   intervals not to
                                   exceed 50 hours
                                   TIS. For all
                                   other airplanes:
                                   inspect within
                                   the next 50 hours
                                   TIS after the
                                   effective date of
                                   this AD and
                                   thereafter at
                                   intervals not to
                                   exceed 50 hours
                                   TIS.
------------------------------------------------------------------------
(2) If any crack is found during  Prior to further    In accordance with
 any inspection required by this   flight after the    the
 AD that is less than 0.24         inspection in       Accomplishment
 inches (6 mm) in length, repair   which the crack     Instructions
 the engine mount assembly. If     is found.           section of Socata
 two repairs on the engine mount                       Service Bulletin
 have already been performed,                          SB 156-71, dated
 replace in accordance with                            May 2001.
 paragraph (d)(3) of this AD.
------------------------------------------------------------------------
(3) If any crack is found during  Prior to further    In accordance with
 any inspection required by this   flight after the    the applicable
 AD that is 0.24 inches (6 mm)     inspection in       maintenance
 or longer in length or if any     which the crack     manual.
 crack is found and two repairs    is found.
 on the engine mount have          Repetitive
 already been performed, replace   inspections are
 the engine mount assembly with    no longer
 part number 892-51-0-035-0 (or    required after
 FAA-approved equivalent part      this replacement.
 number).
------------------------------------------------------------------------
(4) You may terminate the         At any time but it  In accordance with
 repetitive inspections of this    must be done        the applicable
 AD after installing engine        prior to further    maintenance
 mount assembly, part number 892-  flight if any of    manual.
 51-0-035-0 (or FAA-approved       the criteria of
 equivalent part number).          paragraph (d)(3)
                                   are met.
------------------------------------------------------------------------

    (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, 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, Small Airplane Directorate.
    (2) Alternative methods of compliance approved in accordance 
with AD 77-15-06, 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.

    (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

[[Page 64931]]

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) 964-4191. 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 77-15-06, Amendment 39-2975.

    Note 2: The subject of this AD is addressed in French AD 2001-
400(A), dated September 19, 2001.


    Issued in Kansas City, Missouri, on December 6, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-30953 Filed 12-14-01; 8:45 am]
BILLING CODE 4910-13-P