AD 2002-03-13

[Federal Register Volume 67, Number 34 (Wednesday, February 20, 2002)]
[Rules and Regulations]
[Pages 7605-7607]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-3587]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-143-AD; Amendment 39-12654; AD 2002-03-13]
RIN 2120-AA64


Airworthiness Directives; Short Brothers Model SD3-60, SD3-60 
SHERPA, and SD3-SHERPA Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Short Brothers Model SD3-60, SD3-60 SHERPA, and SD3-
SHERPA series airplanes, that requires a one-time inspection of the 
wiring harness and power cables of the heated windshield to detect 
inadequate clearance, inadequate support, or chafing. This amendment 
also requires corrective action (including re-routing for adequate 
clearance or replacing damaged cables, as applicable), if necessary. 
The actions specified by this AD are intended to prevent chafing or 
damage of the power cables of the heated windshield, which could cause 
arcing and result in smoke and fire in the cockpit. This action is 
intended to address the identified unsafe condition.

DATES: Effective March 27, 2002.

[[Page 7606]]

    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 27, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Short Brothers, Airworthiness & Engineering Quality, P.O. 
Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. This 
information may be examined at the Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, 
SW., Renton, Washington; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington, 98055-4056; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Short Brothers Model SD3-60, 
SD3-60 SHERPA, and SD3-SHERPA series airplanes was published in the 
Federal Register on November 23, 2001 (66 FR 58680). That action 
proposed to require a one-time inspection of the two power cables to 
the heated windshield to detect inadequate clearance, chafing, and 
inadequate support. The action also proposed to require corrective 
action, if necessary, including increasing the clearance, providing 
additional support, re-routing, and replacing power cables, as 
applicable.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Explanation of Changes to Final Rule

    The statement of unsafe condition in the ``Summary'' section and 
subsequent sections of this AD have been changed for clarification to 
include a reference to the wiring harness of the power cables and to 
clarify certain wording.
    Paragraph (a) of the proposed rule specifies a general visual 
inspection of the power cables to the heated windshield to detect 
inadequate clearance, chafing, and inadequate support. However, 
paragraph (a) of the proposed rule does not make clear that the 
inspection includes inspecting the wiring harness and ensuring that the 
harness is securely supported. Therefore, for clarification, we have 
changed paragraph (a) of this final rule to require a general visual 
inspection of the wiring harness and power cables of the heated 
windshield to detect inadequate clearance between the cables and the 
flight instruments, and to ensure that the harness is securely 
supported and no chafing of the protective cover on the cables is 
evident.
    In addition, we have changed paragraphs (b), (c), and (d) of the 
proposed rule to paragraphs (a)(1), (a)(2), and (a)(3) in this final 
rule, as they are subparagraphs of paragraph (a), and we have clarified 
certain wording in those paragraphs. We find that these changes do not 
expand the scope of the proposed AD but merely provide clarification of 
the requirements of this AD.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule with the changes described previously. The FAA has determined that 
these changes will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Cost Impact

    The FAA estimates that 78 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the required inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $4,680, or $60 
per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    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.
    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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from 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, pursuant to 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. Section 39.13 is amended by adding the following new 
airworthiness directive:
2002-03-13  Short Brothers PLC: Amendment 39-12654. Docket 2001-NM-
143-AD.

    Applicability: All Model SD3-60, SD3-60 SHERPA, and SD3-SHERPA 
series airplanes; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, 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 (b) 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 the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.


[[Page 7607]]


    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent chafing or damage of the power cables of the heated 
windshield, which could cause arcing and result in smoke and fire in 
the cockpit, accomplish the following:

Inspection and Corrective Action

    (a) Within 90 days after the effective date of this AD: Perform 
a general visual inspection of the wiring harness and power cables 
of the heated windshield to detect inadequate clearance between the 
cables and the flight instruments, and to ensure that the harness is 
securely supported and no chafing of the protective cover on the 
cables is evident, in accordance with Short Brothers Service 
Bulletin SD3 SHERPA-30-2 (for Model SD3 SHERPA series airplanes), 
SD360 SHERPA-30-2 (for Model SD3-60 SHERPA series airplanes), or 
SD360-30-26 (for Model SD3-60 series airplanes); all dated April 2, 
2001; as applicable. If no evidence of chafing is found and 
clearance and support of the power cables is adequate, no further 
action is needed.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (1) If no evidence of chafing is found, but clearance or support 
of the harness is inadequate: Prior to further flight, re-route the 
power cable for adequate clearance or provide additional support of 
the cable harness, as applicable, in accordance with Short Brothers 
Service Bulletin SD3 SHERPA-30-2 (for Model SD3 SHERPA series 
airplanes), SD360 SHERPA-30-2 (for Model SD3-60 SHERPA series 
airplanes), or SD360-30-26 (for Model SD3-60 series airplanes); all 
dated April 2, 2001; as applicable.
    (2) If evidence of chafing is found, but there is no damage to 
the outer nylon protective cover resulting in exposure of the glass 
fiber braid: Prior to further flight, re-route the power cables for 
adequate clearance, in accordance with Short Brothers Service 
Bulletin SD3 SHERPA-30-2 (for Model SD3 SHERPA series airplanes), 
SD360 SHERPA-30-2 (for Model SD3-60 SHERPA series airplanes), or 
SD360-30-26 (for Model SD3-60 series airplanes); all dated April 2, 
2001; as applicable.
    (3) If evidence of chafing is found, and there is damage to the 
outer nylon protective cover resulting in exposure of the glass 
fiber braid: Prior to further flight, replace the damaged power 
cable with a new cable, in accordance with Short Brothers Service 
Bulletin SD3 SHERPA-30-2 (for Model SD3 SHERPA series airplanes), 
SD360 SHERPA-30-2 (for Model SD3-60 SHERPA series airplanes), or 
SD360-30-26 (for Model SD3-60 series airplanes); all dated April 2, 
2001; as applicable.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, International 
Branch, ANM-116.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (d) The actions shall be done in accordance with Short Brothers 
Service Bulletin SD3 SHERPA-30-2, dated April 2, 2001; Short 
Brothers Service Bulletin SD360 SHERPA-30-2, dated April 2, 2001; 
and Short Brothers Service Bulletin SD360-30-26, dated April 2, 
2001; as applicable. This incorporation by reference was approved by 
the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained from Short 
Brothers, Airworthiness & Engineering Quality, P.O. Box 241, Airport 
Road, Belfast BT3 9DZ, Northern Ireland. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

    Note 4: The subject of this AD is addressed in British 
airworthiness directive 001-04-2001.

Effective Date

    (e) This amendment becomes effective on March 27, 2002.

    Issued in Renton, Washington, on February 7, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-3587 Filed 2-19-02; 8:45 am]
BILLING CODE 4910-13-P