AD Amdt-39-10768

[Federal Register Volume 63, Number 182 (Monday, September 21, 1998)]
[Rules and Regulations]
[Pages 50134-50135]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-24904]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-63-AD; Amendment 39-10768; AD 98-20-02]
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 inspections to detect chafing of the hydraulic pipe 
on the emergency uplock release system of the main landing gear (MLG); 
testing of the hydraulic pipe for leaks, if necessary; and repair of 
the hydraulic pipe, if necessary. This amendment also requires 
modification of the attachment bolt and attachment hole on the 
structural panel, which terminates the repetitive inspection 
requirements of this AD. 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 chafing between the hydraulic pipe on the emergency uplock 
release system of the MLG and an attachment bolt on a structural panel, 
which could result in rupture of the hydraulic pipe, loss of hydraulic 
pressure, and consequent inability to activate the emergency MLG 
extension.

DATES: Effective October 26, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 26, 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 
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 April 21, 
1998 (63 FR 19675). That action proposed to require repetitive 
inspections to detect chafing of the hydraulic pipe on the emergency 
uplock release system of the main landing gear (MLG); testing of the 
hydraulic pipe for leaks, if necessary; and repair of the hydraulic 
pipe, if necessary. That action also proposed to require modification 
of the attachment bolt and attachment hole on the structural panel, 
which would terminate the repetitive inspection requirements of this 
AD.
    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.
    The commenter, the manufacturer, indicates that it has issued Saab 
Service Bulletin 2000-29-007, Revision 02, dated May 8, 1998. (The 
proposed AD references Revision 01 of the service bulletin as the 
appropriate source of service information for accomplishment of the 
actions required by the AD.) The commenter notes that Revision 02 of 
the service bulletin contains no changes to compliance or technical 
items; it only specifies a change to the aircraft effectivity. The 
commenter indicates that this effectivity changes does not affect any 
U.S.-registered airplane.
    Based on this comment, the FAA has revised this final rule to 
include Revision 02 of the service bulletin as an additional source of 
service information for accomplishment of the requirements of the AD. 
Additionally, the applicability of this final rule has been revised to 
add airplane serial number -060 (which is not on the U.S. Register), 
and to exclude certain airplane serial numbers, as specified in the 
effectivity of Revision 02 of the service bulletin.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. 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 3 Saab Model SAAB 2000 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 
inspection, and that the average labor rate is $60 per work hour. Based 
on these figures, the cost impact of the inspection on U.S. operators 
is estimated to be $540, or $180 per airplane, per inspection cycle.
    It will take approximately 6 work hours per airplane to accomplish 
the required modification, at an average labor rate of $60 per work 
hour. Required parts will be supplied by the manufacturer at no cost to 
the operators. Based on these figures, the cost impact of the 
modification required by this AD on U.S. operators is estimated to be 
$1,080, or $360 per airplane.
    The cost impact figures discussed above are 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.

[[Page 50135]]

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:

98-20-02  Saab Aircraft AB: Amendment 39-10768. Docket 98-NM-63-AD.

    Applicability: Model SAAB 2000 series airplanes, serial numbers 
-002 through -050 inclusive, and -052, -053, and -060; excluding 
serial number -051; 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 (c) 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.

    Note 2: Accomplishment of the actions required by this AD prior 
to the effective date of this AD in accordance with Saab Service 
Bulletin 2000-29-007, dated April 29, 1997, is considered acceptable 
for compliance with the applicable actions specified in this AD.

    To prevent chafing between the hydraulic pipe on the emergency 
uplock release system of the main landing gear (MLG) and an 
attachment bolt on a structural panel, which could result in rupture 
of the hydraulic pipe, loss of hydraulic pressure, and consequent 
inability to activate the emergency MLG extension, accomplish the 
following:
    (a) Within 300 flight hours after the effective date of this AD, 
perform a visual inspection to detect chafing of the hydraulic pipe 
on the emergency uplock release system of the MLG, in accordance 
with Saab Service Bulletin 2000-29-007, Revision 01, dated August 
18, 1997, or Revision 02, dated May 8, 1998.
    (1) If no chafing is detected, repeat the visual inspection 
thereafter at intervals not to exceed 300 flight hours.
    (2) If any chafing is detected, prior to further flight, perform 
a test of the hydraulic pipe to detect leaks in accordance with the 
service bulletin.
    (i) If no leaking is detected, repeat the actions required by 
paragraph (a) of this AD thereafter at intervals not to exceed 300 
flight hours.
    (ii) If any leaking is detected, prior to further flight, repair 
the hydraulic pipe and accomplish paragraph (b) of this AD, in 
accordance with the service bulletin.
    (b) Within 900 flight hours after the effective date of this AD, 
modify the attachment bolt and attachment hole on the structural 
panel, in accordance with Saab Service Bulletin 2000-29-007, 
Revision 01, dated August 18, 1997, or Revision 02, dated May 8, 
1998. Accomplishment of this modification constitutes terminating 
action for the repetitive inspection requirements of this AD.
    (c) 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 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.

    (d) 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.
    (e) The actions shall be done in accordance with Saab Service 
Bulletin 2000-29-007, Revision 01, dated August 18, 1997, or Saab 
Service Bulletin 2000-29-007, Revision 02, dated May 8, 1998. 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 4: The subject of this AD is addressed in Swedish 
airworthiness directives (SAD) 1-112R1, dated August 21, 1997, and 
1-112R2, dated May 8, 1998.

    (f) This amendment becomes effective on October 26, 1998.

    Issued in Renton, Washington, on September 11, 1998.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-24904 Filed 9-18-98; 8:45 am]
BILLING CODE 4910-13-U