[Federal Register Volume 67, Number 238 (Wednesday, December 11, 2002)]
[Rules and Regulations]
[Pages 76106-76109]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-31128]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-CE-33-AD; Amendment 39-12978; AD 2002-25-03]
RIN 2120-AA64


Airworthiness Directives; Pilatus Britten-Norman Limited BN-2A 
and BN2A Mk. III Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 97-14-
01, which currently applies to all Pilatus Britten-Norman Limited 
(Pilatus Britten-Norman) BN-2A and BN2A Mk. III series airplanes. AD 
97-14-01 requires repetitively inspecting the left-hand rudder bar 
assembly for cracks, measuring the slider tube unit wall thickness, and 
modifying the rudder bar assembly by installing a slider tube unit of 
improved design as a terminating action for the repetitive inspections. 
AD 97-14-01 resulted from mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for the United 
Kingdom. Reports of cracks being found on the

[[Page 76107]]

right-hand rudder bar assembly and the inadvertent omission of 
requiring inspection of the rudder pedal beams prompted this action. 
This AD retains the requirements of AD 97-14-01 and requires 
inspections of the right-hand rudder bar assembly and each rudder pedal 
beam. The actions specified by this AD are intended to prevent failure 
of the pilot's and co-pilot's rudder bar assemblies, which could result 
in loss of control of the airplane during landing operations.

DATES: This AD becomes effective on January 31, 2003.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
January 31, 2003.

ADDRESSES: You may get the service information referenced in this AD 
from B-N Group Limited, Bembridge, Isle of Wight, United Kingdom PO35 
5PR; telephone: +44 (0) 1983 872511; facsimile: +44 (0) 1983 873246. 
You may view this information at the Federal Aviation Administration 
(FAA), Central Region, Office of the Regional Counsel, Attention: Rules 
Docket No. 2002-CE-33-AD, 901 Locust, Room 506, 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: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Discussion

Has FAA Taken Any Action to This Point?

    Reports of failure of the pilot's rudder bar caused FAA to issue AD 
97-14-01 on all Pilatus Britten-Norman BN-2A and BN2A Mk. III series 
airplanes. Fractures of the central pillar/slider tube adjacent to the 
welded transverse lugs caused the pilot's rudder bar to fail. AD 97-14-
01, Amendment 39-10058 (62 FR 35670, July 2, 1997), currently requires 
the following:

--Repetitively inspecting the left-hand rudder bar assembly for cracks;
--Measuring the slider tube unit wall thickness; and
--Modifying the rudder bar assembly by installing a slider tube unit of 
improved design as a terminating action for the repetitive inspections.

What Events Have Happened Since AD 97-14-01 To Cause This AD?

    The Civil Aviation Authority (CAA), which is the airworthiness 
authority for the United Kingdom, recently notified FAA of the need to 
change AD 97-14-01. The CAA reports that fractures in the central 
pillar/slider tube adjacent to the welded transverse lugs have been 
found on the co-pilot's (or dual) rudder bar assembly. These reports 
prompted a need to require inspections of the right-hand rudder bar 
assembly in addition to the left-hand rudder bar assembly. We also 
realized we inadvertently omitted from AD 97-14-01 repetitive 
inspections of the rudder pedal beam as specified in Britten-Norman 
Service Bulletin No. BN-2/SB. 56, Issue 2, dated February 13, 1978.

What Is the Potential Impact if FAA Took No Action?

    This condition, if not corrected, could result in failure of the 
pilot's and co-pilot's rudder bar assemblies. Such failure could result 
in loss of control of the airplane during landing operations.

Has FAA Taken Any Action to This Point?

    We issued a proposal to amend part 39 of the Federal Aviation 
Regulations (14 CFR part 39) to include an AD that would apply to all 
Pilatus Britten-Norman BN-2A and BN2A Mk. III series airplanes. This 
proposal was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on September 18, 2002 (67 FR 58734). The NPRM 
proposed to supersede AD 97-14-01 with a new AD that would retain the 
actions of AD 97-14-01 and require inspections of the right-hand (co-
pilot's) rudder bar assembly and the rudder pedal beams.

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. We did not receive any comments on the proposed rule 
or on our determination of the cost to the public.

FAA's Determination

What Is FAA's Final Determination on This Issue?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We have determined that these minor 
corrections:

--Provide the intent that was proposed in the NPRM for correcting the 
unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 113 airplanes in the U.S. 
registry.

What Is the Cost Impact of This AD on Owners/Operators of the Affected 
Airplanes?

    We estimate the following costs to accomplish the inspection:

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                                                                                          Total cost per
                Labor cost                                  Parts cost                       airplane              Total cost on U.S.  operators
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6 workhours x $60 = $360.................  No parts required..........................              $360   $360 x 113 = $40,680.
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    We estimate the following costs to accomplish any necessary 
replacements that will be required based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need such replacement:

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               Labor cost                   Parts cost                    Total cost per airplane
----------------------------------------------------------------------------------------------------------------
10 workhours x $60 = $600...............         $1,300   $600 + $1,300 = $1,900.
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[[Page 76108]]

Compliance Time of This AD

What Will Be the Compliance Time of This AD?

    The compliance time of this AD is based on number of landings 
rather than hours time-in-service (TIS).

Why Is the Compliance Time Presented in Landings Instead of Hours Time-
in-Service?

    The reason for this type of compliance is that the area that is 
showing fatigue is the pilot's and co-pilot's rudder bar assemblies and 
pillar/slider tube unit. This area of the airplane is used during the 
landing operation. Furthermore, the stress and fatigue is greater in 
the thinner gauged metal slider tube unit upon landing. We will use the 
number of landings as the compliance time for this AD.
    Since airplane operators are not required to keep track of 
landings, we will provide a method of calculating hours TIS into 
landings.

Regulatory Impact

Does This AD Impact Various Entities?

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    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, under 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. FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
97-14-01, Amendment 39-10058 (62 FR 35670, July 2, 1997), and by adding 
a new AD to read as follows:

2002-25-03 Pilatus Britten-Norman Limited: Amendment 39-12978; 
Docket No. 2002-CE-33-AD; Supersedes AD 97-14-01, Amendment 39-
10058.

    (a) What airplanes are affected by this AD? This AD affects the 
Models BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, 
BN-2A-21, BN-2A-26, BN-2A-27, BN2A MK. III, BN2A MK. III-2, and BN2A 
MK. III-3 airplanes, all serial numbers, that are certificated in 
any category.
    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the airplanes identified in paragraph (a) of this AD must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to prevent failure of the pilot's and co-
pilot's rudder bar assemblies, which could result in loss of control 
of the airplane during landing operations.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:
    (1) Right-hand and left-hand slider tube and vertical pillar of 
the rudder bar. Within 500 landings after the last inspection 
required by AD 97-14-01 or the next 100 landings after January 31, 
2003 (the effective date of this AD), whichever occurs later, 
inspect (visually and using a dye penetrant method) the left-hand 
and right-hand slider tube and vertical pillar of the rudder bar 
unit for cracks and measure the slider tube wall to determine 
thickness. Accomplish this inspection and follow-up actions below in 
accordance with the instructions specified in B-N Group Ltd. Service 
Bulletin Number SB 111, Issue 2, dated April 1, 2002 (Part of this 
accomplishment is the incorporation of Britten-Norman Service 
Bulletin No. BN-2/SB. 56, Issue 2, dated February 13, 1978; and 
Britten-Norman Service Bulletin No. BN-2/SB. 111, Issue 1, dated 
October 25, 1977):

------------------------------------------------------------------------
             If                       Then                  When
------------------------------------------------------------------------
(i) No cracks are found       Repetitively inspect  Repetitively inspect
 during the inspection         the left-hand and     at intervals not to
 required in paragraph         right-hand slider     exceed 500 landings
 (d)(1) of this AD and the     tube and vertical     after the initial
 slider tube wall thickness    pillar of the         inspection required
 is 0.056-inch (17 s.w.g.):    rudder bar unit and   in paragraph (d)(1)
                               install               of this AD.
                               Modification NB/M/    Incorporate the
                               948, part number (P/  modification upon
                               N) NB-45-A1-2975 or   the accumulation of
                               FAA-approved          5,000 landings
                               equivalent part       after August 18,
                               number, on the left-  1997 (the effective
                               hand and right-hand   date of AD 97-14-
                               slider tube and       01) or within the
                               vertical pillar of    next 500 landings
                               the rudder bar        after January 31,
                               unit. When this       2003 (the effective
                               modification is       date of this AD),
                               incorporated, the     whichever occurs
                               repetitive            later (unless any
                               inspections in that   crack(s) is/are
                               area may be           found during an
                               terminated.           inspection).
(ii) No cracks are found      Repetitively inspect  Repetitively inspect
 during the inspection         the left-hand and     at intervals not to
 required in paragraph         right-hand slider     exceed 250 landings
 (d)(1) of this AD and the     tube and vertical     after the initial
 slider tube wall thickness    pillar paragraph of   inspection.
 is 0.036-inch (20 s.w.g.):    the rudder bar unit   Incorporate the
                               and install           modification upon
                               Modification NB/M/    the accumulation of
                               948, part number (P/  2,500 landings
                               N) NB-45-A1-2975 or   after August 18,
                               FAA-approved          1997 (the effective
                               equivalent part       date of AD 97-14-
                               number, on the left-  01) or within the
                               hand and right-hand   next 250 landings
                               slider tube and       after January 31,
                               vertical pillar of    2003 (the effective
                               the rudder bar        date of this AD),
                               unit. When this       whichever occurs
                               modification is       later (unless any
                               incorporated, the     crack(s) is/are
                               repetitive            found during an
                               inspections in that   inspection).
                               area may be
                               terminated.

[[Page 76109]]

 
(iii) If any crack(s) is/are  Install Modification  Prior to further
 found during any inspection   NB/M/948, P/N NB-45-  flight after the
 on the left-hand or right-    A1-2975 or FAA-       inspection where
 hand slider tube and          approved equivalent   the crack(s) is/are
 vertical pillar of the        part number, on the   found.
 rudder bar unit:              cracked slider tube
                               and vertical pillar
                               of the rudder bar
                               unit. When this
                               modification is
                               incorporated, the
                               repetitive
                               inspections in that
                               area may be
                               terminated.
------------------------------------------------------------------------

    (2) As of January 31, 2003 (the effective date of this AD), only 
install rudder bar assemblies that incorporate Modification NB/M/
948.
    (3) Rudder pedal beams. Accomplish the following on the rudder 
pedal beams:

------------------------------------------------------------------------
           Action                  Compliance            Procedures
------------------------------------------------------------------------
(i) Inspect (visually and     Inspect within the    In accordance with
 using a dye penetrant         next 100 landings     Britten-Norman
 inspection method) each       after January 31,     Service Bulletin
 rudder pedal beam for         2003 (the effective   No. BN-2/SB. 56,
 cracks and replace any        date of this AD)      Issue 2, dated
 cracked beam with a P/N NB-   and thereafter at     February 13, 1978.
 45-C-2153 (Post Mod No. BB/   intervals not to
 M/341) rudder pedal beam.     exceed 500
                               landings. Replace
                               prior to further
                               flight after the
                               inspection where
                               any crack(s) is/are
                               found. Continue
                               with repetitive
                               inspection
                               intervals.
(ii) Only install P/N NB-45-  As of January 31,     Not Applicable.
 C-2153 (Post Mod No. BB/M/    2003 (the effective
 341) rudder pedal beams.      date of this AD).
------------------------------------------------------------------------


    Note 1: If operators have not recorded the number of landings, 
the landings can be calculated by multiplying 3 landings per 1 hour 
TIS.

    (e) Can I comply with this AD in any other way?
    (1) You may use an alternative method of compliance or adjust 
the compliance time if:
    (i) Your alternative method of compliance provides an equivalent 
level of safety; and
    (ii) The Manager, Standards Office, Small Airplane Directorate, 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Standards Office.
    (2) Alternative methods of compliance approved in accordance 
with AD 97-14-01, which is superseded by this AD, are not approved 
as alternative methods of compliance with this AD.

    Note 2: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Doug Rudolph, Aerospace 
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: 
(816) 329-4090.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (h) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with B-N Group Ltd. Service Bulletin Number SB 111, Issue 2, dated 
April 1, 2002; and Britten-Norman Service Bulletin No. BN-2/SB. 56, 
Issue 2, dated February 13, 1978. The Director of the Federal 
Register approved this incorporation by reference under 5 U.S.C. 
552(a) and 1 CFR part 51. You may get copies from B-N Group Limited, 
Bembridge, Isle of Wight, United Kingdom PO35 5PR; telephone: +44 
(0) 1983 872511; facsimile: +44 (0) 1983 873246. You may view copies 
at the FAA, Central Region, Office of the Regional Counsel, 901 
Locust, Room 506, Kansas City, Missouri, or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (i) Does this AD action affect any existing AD actions? This 
amendment supersedes AD 97-14-01, Amendment 39-10058.

    Note 3: The subject of this AD is addressed in B-N Group Ltd. 
Service Bulletin Number SB 111, Issue 2, dated April 1, 2002. This 
service bulletin is classified as mandatory by the United Kingdom 
Civil Aviation Authority (CAA).

    (j) When does this amendment become effective? This amendment 
becomes effective on January 31, 2003.

    Issued in Kansas City, Missouri, on December 2, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-31128 Filed 12-10-02; 8:45 am]
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