AD Amdt-39-12610 - Airworthiness Directives; Fairchild Aircraft, Inc. SA26, SA226, and SA227 Ser...

Type	Manufacturer	Model	Details
aircraft	Fairchild	Various	Airworthiness Directives; Fairchild Aircraft, Inc. SA26, SA226, and SA227 Series Airplanes

Unsafe Condition

Dual engine flameout on Fairchild Aircraft, Inc. SA226 and SA227 series airplanes, which could result in failure of both engines and loss of control of the airplane.

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Required Actions

Revise the pilot's operating handbook and airplane flight manual (POH/AFM) to incorporate procedures for preventing engine flameout in icing conditions. Modify the torque sensing system to automatically turn on the igniters when low torque is sensed.

AI-generated summary from the source AD text. Verify against the official source before acting.

Compliance Time

Before further flight

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Affected Aircraft

Fairchild Aircraft, Inc. SA226 and SA227 series airplanes.

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Federal Register Abstract

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.

Document Text

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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-1816]

-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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:
<bullet> Will not change the meaning of the AD; and
<bullet> 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:
<bullet> Gives all owners/operators of the affected airplanes
adequate time to schedule and accomplish the actions in this AD; and
<bullet> 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

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

Applicability

Unsafe Condition

Required Actions

Compliance Time

Affected Aircraft

Federal Register Abstract

Document Text