[Federal Register Volume 66, Number 167 (Tuesday, August 28, 2001)]
[Proposed Rules]
[Pages 45196-45198]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21630]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-113-AD]
RIN 2120-AA64


Airworthiness Directives; Short Brothers Model SD3 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Short Brothers Model SD3 
series airplanes. This proposal would 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. This proposal also would require 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: Comments must be received by September 27, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-

[[Page 45197]]

113-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments 
may be inspected at this location between 9:00 a.m. and 3:00 p.m., 
Monday through Friday, except Federal holidays. Comments may be 
submitted via fax to (425) 227-1232. Comments may also be sent via the 
Internet using the following address: [email protected]. 
Comments sent via fax or the Internet must contain ``Docket No. 2001-
NM-113-AD'' in the subject line and need not be submitted in 
triplicate. Comments sent via the Internet as attached electronic files 
must be formatted in Microsoft Word 97 for Windows or ASCII text.
    The service information referenced in the proposed rule 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 FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-113-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-113-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Civil Aviation Authority (CAA), which is the airworthiness 
authority for the United Kingdom, notified the FAA that an unsafe 
condition may exist on certain Short Brothers Model SD3 series 
airplanes. The CAA advises that during Certificate of Airworthiness 
Renewal Flight Tests on these airplanes, the engines failed to reach 
the Reserve Takeoff Power (RTOP) boost specified in the Airplane Flight 
Manual. The cause of this failure is unknown; however, a contributing 
factor could be reduced fuel flow to the engines. If the engines fail 
to reach adequate RTOP boost during takeoff, the flightcrew may 
experience problems maintaining control of the airplane in flight.

Explanation of Relevant Service Information

    The manufacturer has issued Shorts Service Bulletins SD3 SHERPA-71-
2, SD360 SHERPA-71-2, SD360-71-19, and SD330-71-24; all dated February 
5, 2001. The service bulletins describe procedures for 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 to ensure 
correct gas generator rotational speed is achieved. The service 
bulletins also describe procedures for a static reduced power check on 
each engine to ensure correct operation of the reserve takeoff power 
(RTOP) system; and follow-on actions if the system fails to provide 
adequate boost. These actions include, but are not limited to, the 
following:
     A functional check of the RTOP solenoid,
     Replacement of any defective RTOP solenoid with a new 
solenoid,
     Adjustment of the RTOP system,
     Adjustment to the torque of the FCU Ng servo valve,
     Test for leakage or restrictions of the FCU pnuematic 
system, and/or
     Overhaul of the FCU.
    Additionally, Shorts Service Bulletin SD330-71-24 describes 
procedures for repetitive tests (checks) of the FCU to ensure correct 
rigging, and adjustment, if necessary.
    Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition.
    The CAA classified these service bulletins as mandatory and issued 
British airworthiness directives 002-02-2001, 003-02-2001, 004-02-2001, 
and 005-02-2001 in order to assure the continued airworthiness of these 
airplanes in the United Kingdom.

FAA's Conclusions

    These airplane models are manufactured in the United Kingdom and 
are type certificated for operation in the United States under the 
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 
21.29) and the applicable bilateral airworthiness agreement. Pursuant 
to this bilateral airworthiness agreement, the CAA has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of the CAA, reviewed all available information, and determined 
that AD action is necessary for products of this type design that are 
certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would require accomplishment of 
the actions specified in the service bulletins described previously.

Cost Impact

    The FAA estimates that 46 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 3 work 
hours per airplane to accomplish the proposed tests (checks), and that 
the average labor rate is $60 per work hour. Based on these figures, 
the cost impact of the proposed 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

[[Page 45198]]

operator has yet accomplished any of the proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 draft 
regulatory 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, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:


Short Brothers PLC: 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 power 
lever movement of the fuel control unit (FCU) lever to ensure the 
lever is contacting the maximum stop, and adjustment of the FCU 
rigging if the lever is not contacting the stop; an engine ground 
run for correct gas generator rotational speed, and 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 dated February 5, 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 
boost, adjustment to the torque of the FCU Ng servo valve, test for 
leakage or restrictions of the FCU pneumatic system, or overhaul of 
the FCU), per the applicable service bulletin. Repeat the tests 
(checks) after that at intervals not to exceed 90 days.

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 2: 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.

    Note 3: The subject of this AD is addressed in British 
airworthiness directives 002-02-2001, 003-02-2001, 004-02-2001, and 
005-02-2001.


    Issued in Renton, Washington, on August 21, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21630 Filed 8-27-01; 8:45 am]
BILLING CODE 4910-13-U