[Federal Register Volume 68, Number 184 (Tuesday, September 23, 2003)]
[Rules and Regulations]
[Pages 55196-55199]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-23931]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-45-AD; Amendment 39-13313; AD 2003-19-10]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to all Fairchild Aircraft, Inc. (Fairchild Aircraft) SA226 and 
SA227 series airplanes. This AD requires you to inspect the fuel boost 
pump wiring for any chafing, cracked insulation material, or evidence 
of bare wire(s) (referred to herein as damage), and replace any damaged 
wiring. This AD also requires you to install protective tubing around 
the fuel boost pump wiring harness. This AD is the result of reports of 
chafed fuel boost pump wiring to either the inboard or outboard boost 
pump wiring. The actions specified by this AD are intended to prevent 
the fuel boost pump wiring from chafing, which could result in 
electrical arcing. This could serve as an ignition source inside the 
fuel tank and result in fire or explosion.

DATES: This AD becomes effective on November 7, 2003.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
November 7, 2003.

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-45-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?

    The FAA has received reports indicating problems with 6 Fairchild 
Aircraft SA227-AC airplanes. Evidence of chafing to either the inboard 
or outboard fuel boost pump wiring has been found on all 6 airplanes. 
In one case, evidence of arcing between the chafed wiring and the fuel 
check valve was found.
    All airplane models within the Fairchild Aircraft SA226 and SA227 
series incorporate this fuel boost pump wiring design.

What Is the Potential Impact if FAA Took No Action?

    Damage to the fuel boost pump wiring, if not detected and 
corrected, could result in electrical arcing. This could serve as an 
ignition source inside the fuel tank and result in fire or explosion.

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 
Fairchild Aircraft SA226 and SA227 series airplanes. This proposal was 
published in the Federal Register as a notice of proposed rulemaking 
(NPRM) on October 15, 2002, 67 FR 63573. The NPRM proposed to require 
you to inspect the fuel boost pump wiring for any chafing, cracked 
insulation material, or evidence of bare wire(s) (referred to herein as 
damage), and replace any damaged wiring. The NPRM also proposed to 
require you to install protective tubing around the fuel boost pump 
wiring harness.

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. The following presents the comments received on the 
proposal and FAA's response to each comment:

[[Page 55197]]

Comment Issue No. 1: Change the Compliance Times for Performing the 
Inspections

What Is the Commenter's Concern?

    The commenter states that through a check of in-house maintenance 
and inspection personnel data records on the company's fleet of 15 
airplanes, no instances of fuel boost pump wire chafing were found. The 
airplanes in this fleet have flying times ranging from 13,925 hours 
time-in-service (TIS) to 25,815 hours TIS. The commenter suggests that 
the unsafe condition is isolated to one location or area where there is 
a problem with incorrect installation of the fuel boost pumps. The 
commenter also states that the unsafe condition may also be an issue 
related to a specific threshold of hours TIS.
    The commenter states that because of the high usage time of his 
fleet, in conjunction with other scheduled and unscheduled maintenance, 
there may be a negative impact on his fleet's flight schedule.
    The commenter requests the compliance times be changed from within 
the next 3 months or 600 hours TIS, whichever occurs first, to 6 months 
or 1,200 hours TIS, whichever occurs first. The commenter justifies 
this request by referencing the date of the associated manufacturer's 
service letters.

What Is FAA's Response to the Concern?

    We do not concur with the commenter. We have determined from 
testing and service data obtained from the manufacturer that the unsafe 
condition exists in low-time and high-time usage airplanes.
    We have determined that 3 months or 600 hours TIS, whichever occurs 
first, is sufficient time to work the inspection into the owners/
operators inspection program. As with any AD action, we will consider 
compliance time extensions provided they provide an acceptable level of 
safety and are submitted through the alternative method of compliance 
procedures specified in the AD.
    We are not changing the final rule AD action based on this comment.

Comment Issue No. 2: Revise the Cost Impact Section

What Is the Commenter's Concern?

    The commenter does not believe that FAA's estimate of the number of 
workhours necessary to accomplish the actions proposed in the NPRM is 
correct. The commenter does not provide a suggested number of workhours 
with substantiating information.

What Is FAA's Response to the Concern?

    We do not concur. We have coordinated all costs with Fairchild 
Aircraft, Inc.
    We are not changing the final rule AD action based on this comment.

Comment Issue No. 3: Give Credit for Previously Accomplishing the 
Actions Required in the Associated Manufacturer's Service Letters

What Is the Commenter's Concern?

    The commenter states that FAA should make a provision for airplanes 
already in compliance with the associated manufacturer's service 
letters.

What Is FAA's Response to the Concern?

    The FAA agrees and we are changing the final rule AD to provide for 
airplanes that already meet the requirements of the service letters.

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 in the above comment disposition and minor 
editorial corrections. We have determined that this change and 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.

How Does the Revision to 14 CFR Part 39 Affect This AD?

    On July 10, 2002, FAA published a new version of 14 CFR part 39 (67 
FR 47997, July 22, 2002), which governs FAA's AD system. This 
regulation now includes material that relates to special flight 
permits, alternative methods of compliance, and altered products. This 
material previously was included in each individual AD. Since this 
material is included in 14 CFR part 39, we will not include it in 
future AD actions.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 490 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 inspection of the 
fuel boost pump wiring:

----------------------------------------------------------------------------------------------------------------
                                                                                          Total cost on U.S.
                Labor cost                  Parts cost    Total cost per airplane             operators
----------------------------------------------------------------------------------------------------------------
2 workhours x $60 per hour = $120........          $96  $120 + $96 = $216..........  $216 x 490 = $105,840
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    We estimate the following costs to accomplish the installation of 
the convoluted tubing:

----------------------------------------------------------------------------------------------------------------
                                                                                          Total cost on U.S.
                Labor cost                  Parts cost    Total cost per airplane             operators
----------------------------------------------------------------------------------------------------------------
1 workhour x $60 per hour = $60..........          $48  $60 + $48 = $108...........  $108 x 490 = $52,920
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[[Page 55198]]

    The FAA has no method of determining the number of repairs or 
replacements each owner/operator will incur based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need such repair. The extent of damage may vary on each airplane.

Compliance Time of This AD

What Is the Compliance Time of This AD?

    The compliance time of this AD is whichever of the following that 
occurs first:

--Within the next 3 months after the effective date of this AD; or
--Within the next 600 hours time-in-service (TIS) after the effective 
date of this AD.

Why Is the Compliance Time of This AD Presented in Both Hours TIS and 
Calendar Time?

    Chafing damage is a direct result of airplane usage. However, 
chafing damage is not necessarily a result of repetitive airplane 
operation. For example, damage could occur on an affected airplane 
within a short period of airplane operation while you could operate 
another affected airplane for a considerable amount of time without 
experiencing wiring damage. Therefore, to assure that any damaged 
wiring is detected and corrected in a timely manner without 
inadvertently grounding any of the affected airplanes, we are utilizing 
a compliance based upon both hours TIS and calendar time.

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

0
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

0
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]

0
2. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2003-19-10 Fairchild Aircraft, Inc.: Amendment 39-13313; Docket No. 
2000-CE-45-AD.

    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models, all serial numbers, that are certificated 
in any category: SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC 
(C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC(C-26B), 
SA227-PC, and SA227-TT.
    (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 the fuel boost pump wiring from 
chafing, which could result in electrical arcing. This could serve 
as an ignition source inside the fuel tank and result in fire or 
explosion.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following, unless 
already accomplished:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Visually inspect the      Within the next 3     Accomplish the
 left-hand and right-hand      months or within      inspection in
 main/auxiliary fuel boost     the next 600 hours    accordance with the
 pump wiring for evidence of   time-in-service       Accomplishment
 chafing, damage, or exposed   (TIS) after           Instructions in
 bare wire(s).                 November 7, 2003      Fairchild Service
                               (the effective date   Letter 226-SL-023
                               of this AD),          or Fairchild
                               whichever occurs      Service Letter 227-
                               first, unless         SL-039, both dated
                               already               September 6, 2000;
                               accomplished.         or Fairchild
                                                     Service Letter CC7-
                                                     SL-031, pages 1 and
                                                     3 dated September
                                                     6, 2000, and page 2
                                                     dated September 25,
                                                     2000, as
                                                     applicable.
-----------------------------
(2) Replace any chafed,       Prior to further      Accomplish
 damaged or exposed bare       flight after the      replacement(s) in
 wire(s).                      inspection required   accordance with the
                               in paragraph (d)(1)   applicable wiring
                               of this AD, unless    manual as specified
                               already               in the applicable
                               accomplished.         Fairchild Service
                                                     Letter.
-----------------------------
(3) Install HEYCO-FLEX V,     Prior to further      Accomplish the
 Slit Convoluted Tubing,       flight after the      installation in
 part-number (P/N) 1634,       inspection required   accordance with the
 around each fuel boost pump   in paragraph (d)(1)   Accomplishment
 wiring harness.               of this AD, unless    Instructions in
                               already               Fairchild Service
                               accomplished.         Letter 226-SL-023
                                                     or Fairchild
                                                     Service Letter 227-
                                                     SL-039, both dated
                                                     September 6, 2000;
                                                     or Fairchild
                                                     Service Letter CC7-
                                                     SL-031, pages 1 and
                                                     3 dated September
                                                     6, 2000, and page 2
                                                     dated September 25,
                                                     2000, as
                                                     applicable.
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? To use an 
alternative method of compliance or adjust the compliance time, use 
the procedures in 14 CFR 39.19. Send these requests to the Manager, 
Fort Worth Airplane Certification Office (ACO). For

[[Page 55199]]

information on 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.
    (f) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Fairchild Service Letter 226-SL-023 or Fairchild Service Letter 
227-SL-039, both dated September 6, 2000; or Fairchild Service 
Letter CC7-SL-031, pages 1 and 3 dated September 6, 2000, and page 2 
dated September 25, 2000. 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 Fairchild Aircraft, Inc., P.O. 
Box 790490, San Antonio, Texas 78279-0490.
    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.
    (g) When does this amendment become effective? This amendment 
becomes effective on November 7, 2003.

    Issued in Kansas City, Missouri, on September 15, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-23931 Filed 9-22-03; 8:45 am]
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