[Federal Register Volume 61, Number 106 (Friday, May 31, 1996)]
[Rules and Regulations]
[Pages 27253-27255]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-13496]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-102-AD; Amendment 39-9639; AD 96-11-14]
RIN 2120-AA64


Airworthiness Directives; Saab Model SAAB 2000 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Saab Model SAAB 2000 series airplanes. This 
action requires inspections to detect cracking of the lower rib of the 
rudder, and repair, if necessary. This action also provides for an 
optional terminating action, which, if accomplished, terminates the 
repetitive inspection requirement. This amendment is prompted by 
reports of fatigue cracking of the lower rib of the rudder. The actions 
specified in this AD are intended to prevent such fatigue cracking and 
subsequent failure of the primary structure of the rudder, which could 
result in reduced controllability of the airplane.

DATES: Effective June 17, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 17, 1996.
    Comments for inclusion in the Rules Docket must be received on or 
before July 30, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 96-NM-102-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The service information referenced in this AD may be obtained from 
SAAB

[[Page 27254]]

Aircraft AB, SAAB Aircraft Product Support, S-581.88, Linkoping, 
Sweden. This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Ruth E. Harder, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-1721; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: The Luftfartsverket (LFV), which is the 
airworthiness authority for Sweden, recently notified the FAA that an 
unsafe condition may exist on certain Saab Model 2000 series airplanes. 
The LFV advises that it has received reports indicating that cracking 
of the bottom rib of the elevator has been detected on two Model SAAB 
2000 series airplanes. Investigation revealed that, loose pieces of the 
web were found inside the rudder on one airplane. The cause of the 
cracking has been attributed to fatigue. Fatigue cracking and 
subsequent failure of the rudder, if not detected and corrected in a 
timely manner, could result in reduced controllability of the airplane.

Explanation of Relevant Service Information

    Saab has issued Service Bulletin SAAB 2000-55-005, dated February 
2, 1996, which describes procedures for repetitive visual inspections 
to detect cracking of the lower rib of the rudder. The service bulletin 
also describes procedures for a temporary repair of cracking that is 
within certain specified limits. The LFV classified this service 
bulletin as mandatory and issued Swedish airworthiness directive SAD 
No. 1-088-R1 in order to assure the continued airworthiness of these 
airplanes in Sweden.
    Additionally, Saab has issued Service Bulletin 2000-55-006, dated 
April 23, 1996, which describes procedures to modify the elevator by 
reinforcing the lower rib. This modification (Modification No. 5736) 
will prevent failure of the rudder due to fatigue cracking of the lower 
rib. Accomplishment of the modification eliminates the need for the 
repetitive visual inspections. The LFV has approved the technical 
content of this service bulletin.

FAA's Conclusions

    This airplane model is manufactured in Sweden and is 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 LFV has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
LFV, 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 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, this AD is being issued to prevent fatigue 
cracking of the lower rib of the rudder and subsequent failure of the 
primary structure of the rudder. Such failure could result in reduced 
controllability of the airplane. This AD requires repetitive visual 
inspections to detect cracking of the lower rib of the rudder, and 
repair, if necessary. The inspections and certain repairs are required 
to be accomplished in accordance with Saab Service Bulletin 2000-55-
005, described previously. Repair of any cracking detected that is 
beyond the limits specified in that service bulletin is required to be 
accomplished in accordance with a method approved by the FAA.
    This AD also provides for optional modification of the rudder, 
which, if accomplished, constitutes terminating action for the 
repetitive inspection requirements of this AD. If accomplished, the 
modification is required to be accomplished in accordance with SAAB 
Service Bulletin 2000-55-006.
    This is considered to be interim action. The FAA is currently 
considering requiring the installation of the rudder modification that 
will constitute terminating action for the repetitive inspections 
required by this AD. However, the planned compliance time for the 
installation of the modification is sufficiently long so that notice 
and public comment will be practicable.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 96-NM-102-AD.'' The postcard will be date stamped and 
returned to the commenter.

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. -
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an

[[Page 27255]]

emergency regulation under DOT Regulatory Policies and Procedures (44 
FR 11034, February 26, 1979). If it is determined that this emergency 
regulation otherwise would be significant under DOT Regulatory Policies 
and Procedures, a final regulatory evaluation will be prepared and 
placed in the Rules Docket. A copy of it, if filed, 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 USC 106(g), 40113, 44701.


Sec. 39.13   [Amended] -

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

96-11-14  SAAB Aircraft Ab: Amendment 39-9639. Docket 96-NM-102-AD.

    -Applicability: Model SAAB 2000 series airplanes; having serial 
numbers 004 through 039, 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 
otherwise 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 (f) 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 fatigue cracking of the lower rib of the rudder and 
subsequent reduced controllability of the airplane, accomplish the 
following:
    (a) Within 20 days after the effective date of this AD: Perform 
a visual inspection to detect cracking of the lower rib of the 
rudder, in accordance with Saab Service Bulletin 2000-55-005, dated 
February 2, 1996.
    (b) If no cracking is detected: Thereafter, repeat the 
inspection required by paragraph (a) of this AD at intervals not to 
exceed 400 hours time-in-service, in accordance with Saab Service 
Bulletin 2000-55-005, dated February 2, 1996.
    (c) If any cracking is detected that is 25 mm in length or less: 
Prior to further flight, perform a temporary repair in accordance 
with paragraph 2.C. of the Accomplishment Instructions of Saab 
Service Bulletin 2000-55-005, dated February 2, 1996. Thereafter, 
repeat the inspections required by paragraph (a) of this AD at 
intervals not to exceed 7 days. -
    (d) If any cracking is detected that is more than 25 mm in 
length: Prior to further flight, repair it in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate. -
    (e) Modification of the lower rib of the rudder (Modification 
No. 5736), in accordance with Saab Service Bulletin 2000-55-006, 
dated April 23, 1996, constitutes terminating action for the 
repetitive inspection requirements of this AD.
    (f) 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, Standardization Branch, ANM-113. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (g) 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.
    (h) The inspections and temporary repair shall be done in 
accordance with Saab Service Bulletin 2000-55-005, dated February 2, 
1996. 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.
    (i) This amendment becomes effective on June 17, 1996.

    Issued in Renton, Washington, on May 22, 1996.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-13496 Filed 5-30-96; 8:45 am]
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