Airworthiness Directives; Short Brothers Model SD3-30, SD3-60, SD3-60 SHERPA, and SD3 SHERPA Series Airplanes

[Federal Register Volume 63, Number 193 (Tuesday, October 6, 1998)]
[Rules and Regulations]
[Pages 53552-53553]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-26392]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-203-AD; Amendment 39-10813; AD 98-21-05]
RIN 2120-AA64


Airworthiness Directives; Short Brothers Model SD3-30, 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 SD3-30, SD3-60, SD3-60 SHERPA, and SD3 SHERPA series 
airplanes, that requires repetitive visual inspections of the flap 
levers and bracket assembly of the inner flap sub-assembly of the left 
and right wings to detect certain discrepancies; and corrective 
actions, if necessary. This amendment is prompted by mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by this AD are intended to detect and 
correct failure of the levers and bracket assembly, which could result 
in uncommanded retraction of the inner flap assembly and consequent 
reduced controllability of the airplane.

DATES: Effective November 10, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 10, 1998.

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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; 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 SD3-30, SD3-60, SD3-60 SHERPA, 
and SD3 SHERPA series airplanes was published in the Federal Register 
on August 13, 1998 (63 FR 43333). That action proposed to require 
repetitive visual inspections of the flap levers and bracket assembly 
of the inner flap sub-assembly of the left and right wings to detect 
certain discrepancies; and corrective actions, if necessary.

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.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 99 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 5 work hours 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 inspection required by this AD on U.S. operators is 
estimated to be $29,700, or $300 per airplane, per inspection cycle.
    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.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

98-21-05  Short Brothers PLC: Amendment 39-10813. Docket 98-NM-203-
AD.

    Applicability: All Model SD3-30, 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

[[Page 53553]]

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 levers and bracket assembly, which 
could result in uncommanded retraction of the inner flap assembly 
and consequent reduced controllability of the airplane, accomplish 
the following:
    (a) Within 90 days after the effective date of this AD: Perform 
a visual inspection of the levers and bracket assembly of the inner 
flap sub-assembly of the left and right wings to detect 
discrepancies (i.e., corrosion, cracking, protective coating 
breakdown, and inadequate clearances between the forward face of the 
lower levers and the bracket web), in accordance with the applicable 
Shorts service bulletin specified below, all dated January 14, 1997:
    <bullet> SD360-27-26 (for Model SD3-60 series airplanes);
    <bullet> SD360 Sherpa 27-1 (for Model SD3-60 SHERPA series 
airplanes);
    <bullet> SD3 Sherpa 27-2 (for Model SD3 SHERPA series 
airplanes); and
    <bullet> SD3-27-36 (for Model SD3-30 series airplanes).
    (1) If no discrepancy is detected, repeat the visual inspection 
thereafter at intervals not to exceed 4,800 flight hours or 24 
months, whichever occurs earlier.
    (2) If any discrepancy is detected, prior to further flight, 
rework the affected area, and accomplish follow-on corrective 
actions, in accordance with the applicable service bulletin.
    (i) If the reworked parts remain within the allowable rework 
limits specified in the applicable service bulletin, repeat the 
visual inspection of the levers and bracket assembly thereafter at 
intervals not to exceed 1,200 flight hours or 6 months, whichever 
occurs earlier.
    (ii) If any reworked part is outside the allowable rework limits 
specified in the applicable service bulletin, prior to further 
flight, replace the reworked part with a new part. Thereafter, 
repeat the inspection at intervals not to exceed 4,800 flight hours 
or 24 months, whichever occurs earlier.
    (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, FAA, 
Transport Airplane Directorate. 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.

    (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.
    (d) The actions shall be done in accordance with the Shorts 
service bulletins specified below, as applicable:
    <bullet> SD360-27-26, dated January 14, 1997;
    <bullet> SD360 Sherpa 27-1, dated January 14, 1997;
    <bullet> SD3 Sherpa 27-2, dated January 14, 1997; and
    <bullet> SD3-27-36, dated January 14, 1997.
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 3: The subject of this AD is addressed in British 
airworthiness directives 008-01-97, 010-01-97, 011-01-97, and 009-
01-97.

    (e) This amendment becomes effective on November 10, 1998.

    Issued in Renton, Washington, on September 28, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-26392 Filed 10-5-98; 8:45 am]
BILLING CODE 4910-13-U

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