[Federal Register Volume 63, Number 79 (Friday, April 24, 1998)]
[Rules and Regulations]
[Pages 20306-20308]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10595]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-97-AD; Amendment 39-10488; AD 98-09-08]
RIN 2120-AA64


Airworthiness Directives; Avions Pierre Robin Model R3000/160 
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 
applies to all Avions Pierre Robin (Avions) Model R3000/160 airplanes. 
This action requires repetitively inspecting the flap control shaft and 
the welds of the flap levers for cracks; replacing the cracked part, if 
cracks are found; and adjusting the flap travel, if no cracks are 
found. Reports of cracked flap control shafts found during routine 
maintenance prompted this action. The actions specified by this AD are 
intended to prevent cracks on the flap control shaft and around the 
welds of the flap levers, which, if not detected and corrected, could 
result in loss of airplane control during flight.

DATES: Effective May 22, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 22, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before June 22, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket 97-CE-97-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.
    Service information that applies to this AD may be obtained from 
Avions Pierre Robin, 1 route de Troyes 21121 Darois, France; telephone: 
03.80.44.20.50; facsimile: 03.80.35.60.80. This information may also be 
examined at the Federal Aviation Administration (FAA), Central Region, 
Office of the Regional Counsel, Attention: Rules Docket 97-CE-97-AD, 
Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, 
FAA, Small Airplane Directorate, Aircraft Certification Service, 1201 
Walnut, suite 900, Kansas City, Missouri 64106; telephone: (816) 426-
6934, facsimile: (816) 426-2169

SUPPLEMENTARY INFORMATION:

Discussion

    The Direction Generale De L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, recently notified the FAA that an 
unsafe condition may exist on all Avions Model R3000/160 airplanes. The 
DGAC reports that cracks were found on the flap control shaft during 
routine maintenance. These inspections also revealed cracks around the 
welding of the lever on the flap actuator. The DGAC investigation 
revealed that the cracks may be occurring because of fatigued welds.

Relevant Service Information

    Avions has issued service bulletin (SB) No. 141, Rev. 1, dated 
November 6, 1995, which specifies procedures for repetitively 
inspecting the flap control shaft and the welds of the flap levers for 
cracks; replacing the cracked part, if cracks are found; and adjusting 
the flap travel, if no cracks are found.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, including the 
relevant service information, the FAA has determined that AD action 
should be taken to prevent cracks on the flap control shaft and around 
the welds of the flap levers, which, if not detected and corrected, 
could result in loss of airplane control during flight.

Explanation of the Provisions of the AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Avions Model R3000/160 airplanes of the same 
type design, this AD requires repetitively inspecting the flap control 
shaft and the welds of the flap levers for cracks; replacing the 
cracked part, if cracks are found; and adjusting the flap travel, if no 
cracks are found. The actions are to be done in accordance with the 
Accomplishment Instructions in Avions Service Bulletin No. 141, Rev. 1, 
dated November 6, 1995.

Cost Impact

    None of the Avions Model R3000/160 airplanes affected by this 
action are on the U.S. Register. All airplanes included in the 
applicability of this rule currently are operated by non-U.S. operators 
under foreign registry; therefore, they are not directly affected by 
this AD action. However, the FAA considers this rule necessary to 
ensure that the unsafe condition is addressed in the event that any of 
these subject airplanes are imported and placed on the U.S. Register.
    Should an affected airplane be imported and placed on the U.S. 
Register, accomplishment of the required replacement would take 
approximately 9 workhours at an average labor charge of $60 per 
workhour. Parts cost approximately $300 per airplane. Based on these

[[Page 20307]]

figures, the total cost impact of this AD would be $840 per airplane 
that would become registered in the United States.

The Effective Date of This AD

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and 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 No. 97-CE-97-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.
    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 copy of the final 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, 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 a new airworthiness directive 
(AD) to read as follows:

98-09-08  Avions Pierre Robin: Amendment 39-10488; Docket No. 97-CE-
97-AD.

    Applicability: Model R3000/160 airplanes, all serial numbers, 
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 (d) 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 in the body of this AD, unless 
already accomplished.
    To prevent cracks on the flap control shaft and around the welds 
of the flap levers, which, if not detected and corrected, could 
result in loss of airplane control during flight, accomplish the 
following:
    (a) Prior to further flight, inspect the flap control shaft and 
the welds on the flap levers for cracks in accordance with the 
Accomplishment Instructions section in Avions Pierre Robin (Avions) 
Service Bulletin (SB) No. 141, Rev. 1, dated November 6, 1995.
    (1) If cracks are found, replace the cracked part in accordance 
with the Accomplishment Instructions section in Avions SB No. 141, 
Rev. 1, dated November 6, 1995.
    (2) If no cracks are found, check the flap travel, and adjust if 
necessary, in accordance with the Accomplishment Instructions 
section in Avions SB No. 141, Rev. 1, dated November 6, 1995.
    (b) At intervals not to exceed 500 hours time-in-service (TIS) 
after the inspection required in paragraph (a) of this AD, repeat 
paragraphs (a), and (a)(1) and (a)(2) of this, if applicable.
    (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) An alternative method of compliance or adjustment of the 
initial or repetitive compliance times that provides an equivalent 
level of safety may be approved by the Manager, Small Airplane 
Directorate, Aircraft Certification Service, 1201 Walnut, suite 900, 
Kansas City, Missouri 64106. The request shall be forwarded through 
an appropriate FAA Maintenance Inspector, who may add comments and 
then send it to the Manager, Small Airplane Directorate.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Small Airplane Directorate.

    (e) Questions or technical information related to the Avions 
Pierre Robin Service Bulletin No. 141, Rev. 1, dated November 6, 
1995, should be directed to Avions Pierre Robin, 1 route de Troyes 
21121 Darois, France; telephone: 03.80.44.20.50; facsimile: 
03.80.35.60.80. This service information may be examined at the FAA, 
Central Region, Office of the Regional Counsel, Room 1558, 601 E. 
12th Street, Kansas City, Missouri 64106.
    (f) The inspections and replacements required by this AD shall 
be done in accordance with Avions Pierre Robin Service Bulletin No. 
141, Rev. 1, dated November 6, 1995. 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 
Avions Pierre Robin, 1 route de Troyes 21121 Darois, France. Copies 
may be inspected at the FAA, Central Region, Office of the Regional 
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at 
the Office of the Federal Register, 800 North

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Capitol Street, NW, suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in French AD 96-
285(A), dated December 4, 1996.

    (g) This amendment becomes effective on May 22, 1998.

    Issued in Kansas City, Missouri, on April 15, 1998.
James A. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-10595 Filed 4-23-98; 8:45 am]
BILLING CODE 4910-13-U