[Federal Register Volume 66, Number 232 (Monday, December 3, 2001)]
[Rules and Regulations]
[Pages 60145-60147]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-29590]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-113-AD; Amendment 39-12525; AD 2001-24-09]
RIN 2120-AA64


Airworthiness Directives; Short Brothers Model SD3 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 certain Short Brothers Model SD3 series airplanes, that 
requires repetitive tests (checks) of the engine power lever to ensure 
that the fuel control unit (FCU) lever is contacting the maximum stop, 
adjustment of the FCU rigging, if necessary, and an engine ground run 
for correct gas generator rotational speed. This AD also requires a 
static reduced power check on each engine to ensure correct operation 
of the reserve takeoff power (RTOP) system; and follow-on actions, if 
necessary. This action is necessary to prevent failure of the engines 
to reach adequate RTOP boost during takeoff, which could result in 
reduced controllability of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective January 7, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 7, 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 certain Short Brothers Model SD3 
series airplanes was published in the Federal Register on August 28, 
2001 (66 FR 45196). That action proposed to require repetitive tests 
(checks) of the power lever movement of the fuel control unit (FCU) 
lever to ensure the lever is contacting the maximum stop, adjustment of 
the FCU rigging, if necessary, and an engine ground run for correct gas 
generator rotational speed. That action also proposed to require a 
static reduced power check on each engine to ensure correct operation 
of the reserve takeoff power system; and follow-on actions, if 
necessary.

[[Page 60146]]

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.

Remove Repetitive Tests/Checks

    The commenter requests that the FAA revise the proposed AD to 
remove the requirement for repetitive tests (checks) every 90 days. The 
commenter suggests that, after the initial tests, the tests should only 
be repeated after the FCU is replaced or during a ``Hot Section'' 
inspection.
    We do not concur with the commenter's request. The commenter 
provides no justification for its request and no data to support that 
its suggestion would provide an acceptable level of safety. No change 
to the final rule is necessary in this regard.

Explanation of New Relevant Service Information

    Since the issuance of the proposed AD, the manufacturer has issued 
Shorts Service Bulletins SD3 SHERPA-71-2, SD360 SHERPA-71-2, SD360-71-
19, and SD330-71-24; all Revision 1; all dated August 2, 2001. The 
proposed rule referenced the original issues of these service 
bulletins, all dated February 5, 2001, as the appropriate sources of 
service information for accomplishment of the proposed actions. The 
actions in Revision 1 are essentially similar to those in the original 
issue of the service bulletins. Revision 1 of all four service 
bulletins corrects minor errors and clarifies certain procedures for 
the static reduced power check on each engine. Accordingly, the FAA has 
revised paragraph (a) of this final rule to refer to Revision 1 of the 
service bulletins as the appropriate sources of service information for 
the actions required by that paragraph. Also, the FAA has added a new 
Note 2 to this final rule (and re-lettered subsequent notes 
accordingly) to give credit for tests, checks, and follow-on actions 
accomplished before the effective date of this AD per the original 
issue of the applicable service bulletin.

Explanation of Changes to Terminology

    For clarification, the FAA has revised the ``Summary'' section and 
paragraph (a) of the proposed AD to clarify certain terminology 
concerning the test of the engine power lever to ensure that the lever 
is contacting the maximum stop.

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 46 Model SD3 series airplanes of U.S. 
registry will be affected by this AD, that it will take approximately 3 
work hours per airplane to accomplish the required tests (checks), and 
that the average labor rate is $60 per work hour. Based on these 
figures, the cost impact of this AD on U.S. operators is estimated to 
be $8,280, or $180 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:

2001-24-09  Short Brothers PLC: Amendment 39-12525. Docket 2001-NM-
113-AD.

    Applicability: All Model SD3-SHERPA, SD3-60, and SD3-60 SHERPA 
series airplanes; and Model SD3-30 series airplanes having PT6A-45R 
series engines; 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.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the engines to reach adequate reserve 
takeoff power (RTOP) boost during takeoff, which could result in 
reduced controllability of the airplane, accomplish the following:

Repetitive Inspections/Corrective Action

    (a) Within 100 flight cycles or 90 days after the effective date 
of this AD, whichever comes later: Do a test (check) of the engine 
power lever to ensure that the fuel control unit (FCU) lever is 
contacting the maximum stop, and adjust the FCU rigging if the lever 
is not contacting the stop; do an engine ground run for correct gas 
generator rotational speed; and do a static reduced power check on 
each engine to ensure correct operation of the RTOP system; per 
Shorts Service Bulletin SD3 SHERPA-71-2, SD360 SHERPA-71-2, SD360-
71-19, or SD330-71-24; all Revision 1; all dated August 2, 2001; as 
applicable. Before further flight, do any follow-on actions 
necessary (includes a functional check of the RTOP solenoid, 
replacement of any defective RTOP solenoid with a new solenoid, 
adjustment of the RTOP system if system fails to provide adequate

[[Page 60147]]

boost, adjustment to the torque of the FCU Ng servo valve, test for 
leakage or restrictions of the FCU pnuematic system, or overhaul of 
the FCU), per the applicable service bulletin. Repeat the tests 
(checks) after that at intervals not to exceed 90 days.

    Note 2: Tests, checks, and follow-on actions accomplished before 
the effective date of this AD per Shorts Service Bulletin SD3 
SHERPA-71-2, SD360 SHERPA-71-2, SD360-71-19, or SD330-71-24; all 
dated February 5, 2001; as applicable; are acceptable for compliance 
with paragraph (a) of this AD.

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 Shorts Service 
Bulletin SD3 SHERPA-71-2, Revision 1, dated August 2, 2001; Shorts 
Service Bulletin SD360 SHERPA-71-2, Revision 1, dated August 2, 
2001; Shorts Service Bulletin SD360-71-19, Revision 1, dated August 
2, 2001; or Shorts Service Bulletin SD330-71-24, Revision 1, dated 
August 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 directives 002-02-2001, 003-02-2001, 004-02-2001, and 
005-02-2001.

Effective Date

    (e) This amendment becomes effective on January 7, 2002.

    Issued in Renton, Washington, on November 21, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-29590 Filed 11-30-01; 8:45 am]
BILLING CODE 4910-13-U