[Federal Register Volume 68, Number 59 (Thursday, March 27, 2003)]
[Rules and Regulations]
[Pages 14892-14894]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-7185]



[[Page 14892]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-CE-49-AD; Amendment 39-13095; AD 2003-06-07]
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) 2002-
05-04, which applies to certain Socata--Groupe Aerospatiale (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 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 AD retains the 
repetitive inspection and repair requirements of AD 2002-05-04, changes 
the applicability section, removes the terminating action, and requires 
replacement of all part number 892-51-0-035-0 engine mount assemblies. 
The actions specified by this AD are intended to prevent failure of the 
engine mount assembly. Such failure could result in loss of control of 
the airplane.

DATES: This AD becomes effective on May 16, 2003.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of May 
16, 2003.

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) 894-
1160; facsimile: (954) 964-4141. You may view this information at the 
Federal Aviation Administration (FAA), Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2002-CE-49-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 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:
    [sbull] Repetitively inspecting any engine mount assembly that is 
not part number 892-51-0-035-0 (or FAA-approved equivalent part number) 
for cracks;
    [sbull] Repairing cracks that do not exceed a certain length;
    [sbull] 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
    [sbull] 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:
    [sbull] Inspecting the engine mount assembly for cracks at 
repetitive intervals;
    [sbull] Repairing any cracks found; and
    [sbull] 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]nrale de l'Aviation Civile (DGAC), 
which is the 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 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 
certain 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 24, 2002 (67 FR 78394). The NPRM proposed 
to supersede AD 2002-05-04 with a new AD that would:
    [sbull] Retain the repetitive inspection and repair requirements of 
AD 2002-05-04;
    [sbull] Remove the terminating action;
    [sbull] Change the applicability section; and
    [sbull] Require replacement of all part number 892-51-0-035-0 
engine mount assemblies with an FAA-approved equivalent part number.

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

[[Page 14893]]

proposed except for minor editorial corrections. We have determined 
that these minor corrections:
    [sbull] Provide the intent that was proposed in the NPRM for 
correcting the unsafe condition; and
    [sbull] Do not add any additional burden upon the public than was 
already proposed in the NPRM.

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 inspections:

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                                                                 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 the 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 the 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
----------------------------------------------------------------------------------------------------------------
20 workhours x $60 = $1,200........  Approximately $3,360.......  $1,200 + 3,360 = $4,560.
----------------------------------------------------------------------------------------------------------------

What Is the Difference Between the Cost Impact of This AD and the Cost 
Impact of AD 2002-05-04?

    The differences between this 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 AD action does 
increase the cost impact over that required by AD 2002-05-04.

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) 
2002-05-04, Amendment 39-12672 (67 FR 10831, March 11, 2002), and by 
adding a new AD to read as follows:

2003-06-07 Socata--Groupe Aerospatiale: Amendment 39-13095; 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:

------------------------------------------------------------------------
                 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 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 14894]]



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               Actions                             Compliance                            Procedures
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(1) Replace any part number 892-51-0- Within the next 50 hours time-in-     In accordance with the applicable
 035-0 engine mount assembly with an   service (TIS) after May 16, 2003      maintenance manual.
 FAA-approved assembly that is not     (the effective date of this AD).
 part number 892-51-0-035-0.
(2) Inspect the engine mount          Initially inspect at whichever of     In accordance with the
 assembly for cracks.                  the following occurs later: after     Accomplishment Instructions section
                                       accumulating 50 hours TIS after       of Socata Service Bulletin SB 156-
                                       engine mount assembly installation;   71, dated May 2001.
                                       within the next 20 hours TIS after
                                       May 16, 2003 (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 any  Prior to further flight after the     In accordance with the
 inspection required by paragraph      inspection in which the crack is      Accomplishment Instructions section
 (d)(2) of this AD that is less than   found.                                of Socata Service Bulletin SB 156-
 0.24 inches (6 mm) in length,                                               71, dated May 2001.
 repair the engine mount assembly.
 If two repairs on the engine mount
 have already been performed, repair
 in accordance with paragraph (d)(4)
 of this AD.
(4) If any crack is found during any  Prior to further flight after the     In accordance with the repair scheme
 inspection required by this AD that   inspection in which the crack is      obtained from Socata Groupe
 is 0.24 inches (6 mm) or longer in    found.                                Aerospatiale, Customer Support,
 length, or if any crack is found                                            Aerodrome Tarbes-Ossun-Lourdes, BP
 and two repairs on the engine mount                                         930-F65009 Tarbes Cedex, France; or
 have already been performed:                                                the Product Support Manager,
(i) Obtain a repair scheme from the                                          Socata--Groupe Aerospatiale, North
 manufacturer through the FAA at the                                         Perry Airport, 7501 Pembroke Road,
 address specified in paragraph (f)                                          Pembroke Pines, Florida 33023.
 of this AD; and                                                             Obtain this repair scheme through
(ii) Incorporate this repair scheme.                                         the FAA at the address specified in
                                                                             paragraph (f) of this AD.
(5) Do not install on any airplane    As of May 16, 2003 (the effective     Not applicable.
 engine mount assembly part number     date of this AD).
 892-51-0-035-0.
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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.

    (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 may get copies 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 view 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.

    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.

    (i) Does this AD action affect any existing AD actions? This 
amendment supersedes AD 2002-05-04, Amendment 39-12672.
    (j) When does this amendment become effective? This amendment 
becomes effective on May 16, 2003.

    Issued in Kansas City, Missouri, on March 19, 2003.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-7185 Filed 3-26-03; 8:45 am]
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