[Federal Register Volume 67, Number 20 (Wednesday, January 30, 2002)]
[Rules and Regulations]
[Pages 4335-4338]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-1816]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-36-AD; Amendment 39-12610, AD 2002-01-16]
RIN 2120-AA64


Airworthiness Directives; Fairchild Aircraft, Inc. SA26, SA226, 
and SA227 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 86-24-
11 and AD 86-25-04, which require you to incorporate, into the 
Limitations Section of the pilot's operating handbook and airplane 
flight manual (POH/AFM) of Fairchild Aircraft, Inc. (Fairchild 
Aircraft) SA226 and SA227 series airplanes, procedures for preventing 
an engine flameout while in icing conditions. This AD retains the POH/
AFM requirements from the above-referenced AD's and requires a 
modification to the torque sensing system to allow the igniters to 
automatically turn on when an engine senses low torque. This AD is the 
result of two instances of a dual engine flameout on the affected 
airplanes. When the torque sensing system modification is incorporated, 
the POH/AFM requirements are no longer necessary. The actions specified 
by this AD are intended to prevent a dual engine flameout on the 
affected airplanes by providing a system that automatically turns on 
the engine igniters when low torque is sensed. A dual engine flameout 
could result in failure of both engines with consequent loss of control 
of the airplane.

DATES: This AD becomes effective on March 11, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of March 
11, 2002.

ADDRESSES: You may get the service information referenced in this AD 
from Fairchild Aircraft, Inc., P.O. Box 790490, San Antonio, Texas 
78279-0490; telephone: (210) 824-9421; facsimile: (210) 820-8609. You 
may view this information at the Federal Aviation Administration (FAA), 
Central Region, Office of the Regional Counsel,Attention: Rules Docket 
No. 2000-CE-36-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: Ingrid Knox, Aerospace Engineer, FAA, 
Airplane Certification Office, 2601 Meacham Boulevard, Fort Worth, 
Texas 76193-0150; telephone: (817) 222-5139; facsimile: (817) 222-5960.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

    Several occurrences of dual-engine flameout on aircraft caused FAA 
to examine the service history of certain type-certificated airplanes. 
Among those examined were the Fairchild Aircraft SA26, SA226, and SA227 
series airplanes.
    Our analysis reveals the following:

--Two incidents of dual-engine flameout on Fairchild Aircraft SA227 
series airplanes; and
--The incidents are unique to the specific airplane configuration and 
not the generic engine installation.

What Are the Consequences if the Condition Is Not Corrected?

    A dual engine flameout could result in failure of both engines with 
consequent 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 Fairchild Aircraft SA26, SA226, and SA227 series airplanes. 
This proposal was published in the Federal Register as a notice of 
proposed rulemaking (NPRM) on May 30, 2001 (66 FR 29268). The NPRM 
proposed to require you to incorporate a kit that would modify the 
torque sensing system to allow the igniters to automatically turn on 
when an engine senses low torque.

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 the FAA's determination of the cost to the public.
    During the comment period, we realized that the following AD's 
relate to this subject:

--AD 86-24-11, Amendment 39-5481, which applies to Fairchild Aircraft 
SA226 series airplanes; and
--AD 86-25-04, Amendment 39-5485, which applies to Fairchild SA227 
series airplanes.


[[Page 4336]]


    These AD's require you to incorporate, into the Limitations Section 
of the pilot's operating handbook and airplane flight manual (POH/AFM) 
of Fairchild Aircraft, Inc. (Fairchild Aircraft) SA226 and SA227 series 
airplanes, procedures for preventing an engine flameout while in icing 
conditions.
    When the torque sensing system modification is incorporated, the 
POH/AFM requirements are no longer necessary. Therefore, we are 
superseding these AD's in this action.

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 
the change described above and minor editorial corrections. We 
determined that these changes:
     Will not change the meaning of the AD; and
     Will not add any additional burden upon the public than 
was already proposed.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 259 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 the modification:

----------------------------------------------------------------------------------------------------------------
                                                                                           Total cost on U.S.
            Labor cost                    Parts cost          Total cost per airplane          operators
----------------------------------------------------------------------------------------------------------------
16 workhours  x  $60 per hour =    Ranges between $1,726     $4,960 per airplane.....                 $1,284,640
 $960.                              and $6,873 per airplane
                                    (we will use a figure
                                    of $4,000).
----------------------------------------------------------------------------------------------------------------

Compliance Time of This AD

What is the Compliance Time of This AD?

    The compliance time of the required modification is within the next 
6 calendar months after the effective date of this AD.

Why Is the Compliance Time Presented in Calendar Time Instead of Hours 
Time-In-Service (TIS)?

    Although a dual-engine flameout could only occur on the affected 
airplanes during airplane operation, the condition is not directly 
related to airplane usage. The condition exists on the airplanes 
regardless of whether the airplane has accumulated 50 hours time-in-
service (TIS) or 5,000 hours TIS.
    The FAA has determined that the 6-calendar-month compliance time:
     Gives all owners/operators of the affected airplanes 
adequate time to schedule and accomplish the actions in this AD; and
     Ensures that the unsafe condition referenced in this AD 
will be corrected within a reasonable time period without inadvertently 
grounding any of the affected airplanes.

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 both Airworthiness Directive 
(AD) 86-24-11, Amendment 39-5481, and AD 86-25-04, Amendment 39-5485; 
and by adding a new AD to read as follows:

2002-01-16  Fairchild Aircraft, Inc.: Amendment 39-12610, Docket No. 
2000-CE-36-AD; Supersedes AD 86-24-11, Amendment 39-5481, and AD 86-
25-04, Amendment 39-5485.

    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models and serial numbers that are certificated 
in any category:

[[Page 4337]]



------------------------------------------------------------------------
           Model                           Serial numbers
------------------------------------------------------------------------
SA26-AT...................  AT100 through AT180E.
SA226-AT..................  AT001 through AT074.
SA226-T...................  T201 through T275, and T277 through T291.
SA226-T(B)................  T276 and T292 through T417.
SA226-TC..................  TC201 through TC419.
SA227-AC..................  AC406, AC415, AC416, AC420 through AC633,
                             AC637, AC638, AC641 through AC644, AC647,
                             AC648, AC651, AC652, AC656, and AC657.
SA227-AT..................  AT423 through AT631.
SA227-TT..................  TT421 through TT547.
------------------------------------------------------------------------

    (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 prevent a dual engine flameout on the 
affected airplanes by providing a system that automatically turns on 
the engine igniters when low torque is sensed. A dual engine 
flameout could result in failure of both engines with consequent 
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) Incorporate, into the     For all airplanes     Procedures are
 Limitations Section of the    except for the        included in
 pilot's operating handbook    Model SA26-AT         Appendix 1 and
 and airplane flight manual    airplanes: within     Appendix 2 of the
 (POH/AFM), the procedures     the next 50 hours     AD.
 included as Appendix 1 or     time-in-service
 Appendix 2 of this AD, as     (TIS) after
 applicable. Following these   December 15, 1986
 procedures is intended to     (the effective date
 prevent an engine flameout    of AD 86-24-11 and
 while in icing conditions.    AD 86-25-04),
                               unless already
                               accomplished
                               (compliance with
                               either AD 86-24-11
                               or AD 86-25-04, as
                               applicable). For
                               the Model SA26-AT
                               airplanes: within
                               the next 50 hours
                               TIS after March 11,
                               2002 (the effective
                               date of this AD).
------------------------------------------------------------------------
(2) Incorporate the kit       Within the next 6     Accomplish the
 specified in the applicable   calendar months       modification in
 service bulletin. This kit    after March 11,       accordance with the
 modifies the torque sensing   2002 (the effective   instructions
 system to allow the           date of this AD).     provided with the
 igniters to automatically                           kit that is
 turn on when an engine                              referenced in
 senses low torque.                                  either Fairchild
                                                     Aircraft Service
                                                     Bulletin 26-74-30-
                                                     048 (FA Kit Drawing
                                                     26K82301), Revised:
                                                     April 13, 2000;
                                                     Fairchild Aircraft
                                                     Service Bulletin
                                                     No. 226-74-003 (FA
                                                     Kit Drawing
                                                     27K82087), Issued:
                                                     March 21, 2000;
                                                     Fairchild Aircraft
                                                     Service Bulletin
                                                     227-74-003 (FA Kit
                                                     Drawing 27K82087),
                                                     Issued: March 21,
                                                     2000; or Fairchild
                                                     Aircraft Service
                                                     Bulletin 227-74-
                                                     001, Issued: July
                                                     8, 1986, as
                                                     applicable.
------------------------------------------------------------------------
(3) You may remove the POH/   You may remove the    Not applicable.
 AFM procedures as required    procedures at any
 by paragraph (1) of this AD   time after
 after accomplishing the       accomplishing the
 modification required in      modification. You
 paragraph (d)(2) of this AD.  can accomplish the
                               modification at any
                               time, but you must
                               accomplish it
                               within the next 6
                               calendar months
                               after March 11,
                               2002 (the effective
                               date of this AD).
------------------------------------------------------------------------


    Note 1: The POH/AFM procedures that are included in Appendix 1 
and Appendix 2 of this AD (required by paragraph (d)(1) of this AD) 
are retained from AD 86-24-11, Amendment 39-5481, and AD 86-25-04, 
Amendment 39-5485. No further action is required by paragraph (d)(1) 
of this AD if you are already in compliance with AD 86-24-11 or AD 
86-25-04. As specified in paragraph (d)(3) of this AD, these POH/AFM 
procedures are no longer necessary after accomplishment of the 
modification in paragraph (d)(2) of this AD.

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Fort Worth Airplane Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Fort Worth ACO.

    Note 2: 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 Ingrid Knox, Aerospace 
Engineer, FAA, Airplane Certification Office, 2601 Meacham 
Boulevard, Fort Worth, Texas 76193-0150; telephone: (817) 222-5139; 
facsimile: (817) 222-5960.
    (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? The modification required by this AD must be done in 
accordance with instructions provided with the kit that is 
referenced in either Fairchild Aircraft Service Bulletin 26-74-30-
048 (FA

[[Page 4338]]

Kit Drawing 26K82301), Revised: April 13, 2000; Fairchild Aircraft 
Service Bulletin No. 226-74-003 (FA Kit Drawing 27K82087), Issued: 
March 21, 2000; Fairchild Aircraft Service Bulletin 227-74-003 (FA 
Kit Drawing 27K82087), Issued: March 21, 2000; or Fairchild Aircraft 
Service Bulletin 227-74-001, Issued: July 8, 1986, as applicable. 
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 Fairchild Aircraft, Inc., P.O. Box 790490, San Antonio, 
Texas 78279-0490. You can view this information 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) When does this amendment become effective? This amendment 
becomes effective on March 11, 2002.

Appendix 1--Supplement to the POH/AFM for Fairchild Aircraft Models 
SA26-AT, SA226-AT, SA226-T, SA226-T(B), and SA226-TC Airplanes

    The IGNITION MODE switches shall be selected to AUTO/CONT during 
all operations in actual or potential icing conditions described 
herein:
    (1) During takeoff and climb out in actual or potential icing 
conditions.
    *(2) When ice is visible on, or shedding from propeller(s), 
spinner(s), or leading edge(s).
    *(3) Before selecting ANTI-ICE, when ice has accumulated.
    (4) Immediately, any time engine flameout occurs as possible 
result of ice ingestion.
    (5) During approach and landing while in or shortly following 
flight in actual or potential icing conditions.

    *Note: If icing conditions are entered in flight without the 
engine anti-icing system having been selected, switch one ENGINE 
system to an ENGINE HEAT position. If the engine runs 
satisfactorily, switch the second ENGINE system to an ENGINE HEAT 
position and check that the second engine continues to run 
satisfactorily.

    For the purpose of this POH/AFM supplement, the following 
definition applies:
    ``Potential icing conditions in precipitation or visible 
moisture meteorological conditions:
    (1) Begin when the OAT is plus 5 degrees C (plus 41 degrees F) 
or colder, and
    (2) End when the OAT is plus 10 degrees C (plus 50 degrees F) or 
warmer.''
    The procedures and conditions described in this appendix 
supersede any other POH/AFM procedures or conditions.

Appendix 2--Supplement to the POH/AFM for Fairchild Aircraft Models 
SA227-AC, SA227-AT, and SA226-TT Airplanes

    The IGNITION MODE switches shall be selected to OVERRIDE or, for 
those aircraft which have the auto-relite system installed, 
CONTINUOUS OR AUTO during all operations in actual or potential 
icing conditions described herein:
    (1) During takeoff and climb out in actual or potential icing 
conditions.
    *(2) When ice is visible on, or shedding from propeller(s), 
spinner(s), or leading edge(s).
    *(3) Before selecting ANTI-ICE, when ice has accumulated.
    (4) Immediately, any time engine flameout occurs as possible 
result of ice ingestion.
    (5) During approach and landing while in or shortly following 
flight in actual or potential icing conditions.

    *Note: If icing conditions are entered in flight without the 
engine anti-icing system having been selected, switch one ENGINE 
system to an ENGINE HEAT position. If the engine runs 
satisfactorily, switch the second ENGINE system to an ENGINE HEAT 
position and check that the second engine continues to run 
satisfactorily.

    For the purpose of this POH/AFM supplement, the following 
definition applies:
    ``Potential icing conditions in precipitation or visible 
moisture meteorological conditions:
    (1) Begin when the OAT is plus 5 degrees C (plus 41 degrees F) 
or colder, and
    (2) End when the OAT is plus 10 degrees C (plus 50 degrees F) or 
warmer.''
    The procedures and conditions described in this appendix 
supersede any other POH/AFM procedures or conditions.

    Issued in Kansas City, Missouri, on January 17, 2002.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-1816 Filed 1-29-02; 8:45 am]
BILLING CODE 4910-13-U