AD 2002-05-04

[Federal Register Volume 67, Number 47 (Monday, March 11, 2002)]
[Rules and Regulations]
[Pages 10831-10833]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-5526]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-41-AD; Amendment 39-12672; AD 2002-05-04]
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: Final rule.

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SUMMARY: This amendment supersedes 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 
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 AD retains the 
inspection and repair requirements of the current AD and adds the 
information communicated by the French airworthiness authority. 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.

DATES: This AD becomes effective on April 22, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of April 
22, 2002.

ADDRESSES: You may get the service information 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) 893-
1400; facsimile: (954) 964-4191. You may view this information at the 
Federal Aviation Administration (FAA), Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2001-CE-41-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the 
Federal Register, 800 North Capitol Street, NW, suite 700, Washington, 
DC.

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:

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. AD 77-15-06 currently requires 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.

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.

What Is the Potential Impact if FAA Took No Action?

    This condition, if not detected and corrected, could cause the 
engine mount assembly to fail. Such failure could result in loss of 
control of the airplane.

Has FAA Taken Any Action to This Point?

    We issued a proposal to amend part 39 of the Federal Aviation 
Regulations (14 CFR part 39) to include an AD that would apply to all 
Socata Models MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 
894E, Rallye 150T, and Rallye 150ST airplanes. This proposal was 
published in the Federal Register as a notice of proposed rulemaking 
(NPRM) on December 17, 2001 (66 FR 64928). The NPRM proposed to 
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.

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. We did not receive any comments on the proposed rule 
or on our determination of the cost to the public.

FAA's Determination

What Is FAA's Final Determination on This Issue?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We have determined that these minor 
corrections:

--Provide the intent that was proposed in the NPRM for correcting the 
unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

[[Page 10832]]

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 81 airplanes in the U.S. registry.

What Is the Cost Impact of This AD on Owners/Operators of the Affected 
Airplanes?

    We estimate the following costs to accomplish each inspection:

----------------------------------------------------------------------------------------------------------------
                                                            Total cost per
             Labor cost                    Parts cost          airplane         Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
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 will be required based on the results of each inspection. We have 
no way of determining the number of airplanes that may need such 
repair:

------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                   Parts cost          airplane
------------------------------------------------------------------------
3 workhours  x  $60 = $180........  No parts required...            $180
------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
replacements that will be required based on the results of each 
inspection. We have no way of determining the number of airplanes that 
may need such replacement:

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

Regulatory Impact

Does This AD Impact Various Entities?

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.

Does This 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) 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 final evaluation prepared for this 
action is contained 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 
77-15-06, Amendment 39-2975, and by adding a new AD to read as follows:

2002-05-04  SOCATA--Groupe AEROSPATIALE: Amendment 39-12672; 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 No.
------------------------------------------------------------------------
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 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:

[[Page 10833]]



------------------------------------------------------------------------
             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      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 April
                                   22, 2002 (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 April
                                   22, 2002 (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 mounts 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 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) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Socata Service Bulletin SB 156-71, dated May 2001. The Director 
of the Federal Register approved this incorporation by reference 
under 5 U.S.C. 552(a) and 1 CFR part 51. You can get copies from 
SOCATA Groupe AEROSPATIALE, Customer Support, Aerodrome Tarbes-
Ossun-Lourdes, BP 930--F65009 Tarbes Cedex, France; or the Product 
Support Manager, SOCATA Groupe AEROSPATIALE, North Perry Airport, 
7501 Pembroke Road, Pembroke Pines, Florida 33023. You can look at 
copies at the FAA, Central Region, Office of the Regional Counsel, 
901 Locust, Room 506, Kansas City, Missouri, or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (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.

    (j) When does this amendment become effective? This amendment 
becomes effective on April 22, 2002.

    Issued in Kansas City, Missouri, on March 1, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-5526 Filed 3-8-02; 8:45 am]
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