[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34583-34585]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16499]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-145-AD; Amendment 39-10622; AD 98-13-31]
RIN 2120-AA64


Airworthiness Directives; Saab Model SAAB 2000 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 Saab Model SAAB 2000 series airplanes, that 
requires repetitive visual inspections to detect discrepancies of the 
bushing installation of the aileron actuation fitting, and eventual 
installation of staked bushings in the fitting. Accomplishment of such 
installation terminates the repetitive inspections. This amendment also 
provides for an optional temporary preventive action, which, if 
accomplished, would allow the repetitive inspection intervals to be 
extended until the terminating action is accomplished. This amendment 
is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by this AD are intended to prevent failure of the fitting 
lugs due to vibration caused by loose bushings in the fittings, and 
consequent reduced controllability of the airplane.

DATES: Effective July 30, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 30, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from SAAB Aircraft AB, SAAB Aircraft Product Support, S-
581.88, Linkoping, Sweden. 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

[[Page 34584]]

Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Saab Model SAAB 2000 
series airplanes was published in the Federal Register on December 11, 
1997 (62 FR 65231). That action proposed to require repetitive visual 
inspections to detect discrepancies of the bushing installation of the 
aileron actuation fitting, and eventual installation of staked bushings 
in the fitting. Accomplishment of such installation terminates the 
repetitive inspections. That action also proposed to provide for an 
optional temporary preventive action, which, if accomplished, allows 
the repetitive inspection intervals to be extended until the 
terminating action is accomplished.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter supports the proposed rule.
    One commenter, the manufacturer, requests that the repair specified 
in paragraph (c) of the proposed rule be accomplished in accordance 
with Saab Service Bulletin 2000-57-014 or the commenter's Repair 
Statements. The commenter states that its Repair Statements are 
approved based on privileges granted by Luftfartsverket (LFV), which is 
the airworthiness authority for Sweden, as part of the production 
certificate for Model SAAB 2000 series airplanes.
    The FAA concurs partially. The FAA does concur that it is 
appropriate to allow repairs in accordance with the service bulletin, 
since no repair is specified in the service bulletin for the condition 
specified in paragraph (c) of this AD. However, in light of the type of 
repair that would be required to address the identified unsafe 
condition, and in consonance with existing bilateral airworthiness 
agreements, the FAA has determined that a repair approved by the FAA, 
the LFV, or the LFV's delegated agent is acceptable for compliance with 
the AD.
    Additionally, the FAA has included the phrase ``prior to further 
flight'' in paragraph (c) of the final rule. This phrase was omitted 
inadvertently from the proposal.

Conclusion

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

Cost Impact

    The FAA estimates that 1 airplane of U.S. registry will be affected 
by this AD.
    The FAA estimates that it will take approximately 1 work hour 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 
required inspection on the single U.S. operator is estimated to be $60 
per airplane, per inspection cycle.
    The FAA estimates that it will take approximately 4 work hours to 
accomplish the required installation, and that the average labor rate 
is $60 per work hour. Required parts will be provided by the 
manufacturer at no cost to the operator. Based on these figures, the 
cost impact of the required installation on the single U.S. operator is 
estimated to be $240 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no 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.
    Should an operator elect to accomplish the optional temporary 
preventive action provided by this AD, it would take approximately 1 
work hour to accomplish it, at an average labor rate of $60 per work 
hour. Required parts would be provided by the manufacturer at no cost 
to the operator. Based on these figures, the cost impact of the 
optional temporary preventive action would be $60 per airplane.

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:

98-13-31 SAAB Aircraft: Amendment 39-10622. Docket 97-NM-145-AD.

    Applicability: Model SAAB 2000 series airplanes having serial 
numbers -002 through -023 inclusive, 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 (e) 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 fitting lugs, due to vibration caused 
by loose bushings in the aileron actuation fittings, which could 
result in reduced controllability of the airplane; accomplish the 
following:
    (a) Within 100 flight hours after the effective date of this AD, 
inspect the bushing installations of the left-hand and right-hand 
aileron actuation fittings to detect any discrepancies, in 
accordance with Saab Service Bulletin 2000-57-014, Revision 02, 
dated February 11, 1997.
    (1) If no discrepancy is found, repeat the inspection thereafter 
at intervals not to exceed 300 flight hours until the requirements 
of paragraph (b) of this AD have been accomplished. Accomplishment 
of the

[[Page 34585]]

temporary preventive action specified in paragraph 2.E. of the 
Accomplishment Instructions of the service bulletin allows the 
repetitive inspections to be accomplished at intervals of 600 flight 
hours until the requirements of paragraph (b) of this AD have been 
accomplished.
    (2) If any discrepancy is found, prior to further flight, 
accomplish the requirements of either paragraph (a)(2)(i) or 
(a)(2)(ii) of this AD in accordance with the service bulletin.
    (i) Except as specified in paragraph (c), accomplish the 
installation required by paragraph (b) of this AD. Accomplishment of 
this installation constitutes terminating action for the 
requirements of this AD. Or
    (ii) Accomplish the temporary preventive action specified in 
paragraph 2.E. of the Accomplishment Instructions of the service 
bulletin. Thereafter, repeat the inspection required by paragraph 
(a) of this AD at intervals not to exceed 600 flight hours until the 
requirements of paragraph (b) of this AD have been accomplished.
    (b) Except as specified in paragraph (c) of this AD, within 
3,000 flight hours after the effective date of this AD, install the 
new staked bushings in the aileron actuation fitting in accordance 
with Saab Service Bulletin 2000-57-014, Revision 02, dated February 
11, 1997. Accomplishment of this installation terminates the 
requirements of this AD.
    (c) If, during the accomplishment of the installation required 
by paragraph (a)(2)(i) or paragraph (b) of this AD, the diameter of 
the small hole of the fitting lug is found to be outside the limits 
specified in Saab Service Bulletin 2000-57-014, Revision 02, dated 
February 11, 1997, prior to further flight, repair it in accordance 
with a method approved by either the Manager, International Branch, 
ANM-116, FAA, Transport Airplane Directorate, or the Luftfartsverket 
(or its delegated agent).
    (d) As of the effective date of this AD, no person shall install 
on any airplane an aileron having part number, 7357995-843 (left-
hand) or 7357995-844 (right-hand), unless it has been modified in 
accordance with paragraph (b) of this AD.
    (e) 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. 
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.
    (f) 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.
    (g) Except as provided in paragraph (c) of this AD, the actions 
shall be done in accordance with Saab Service Bulletin 2000-57-014, 
Revision 02, dated February 11, 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 SAAB Aircraft AB, SAAB Aircraft Product Support, S-
581.88, Linkoping, Sweden. 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 Swedish 
airworthiness directive (SAD) No. 1-102R1, dated November 8, 1996.

    (h) This amendment becomes effective on July 30, 1998.

    Issued in Renton, Washington, on June 16, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-16499 Filed 6-24-98; 8:45 am]
BILLING CODE 4910-13-U