[Federal Register Volume 67, Number 181 (Wednesday, September 18, 2002)]
[Proposed Rules]
[Pages 58734-58737]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-23653]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 67, No. 181 / Wednesday, September 18, 2002 / 
Proposed Rules  

[[Page 58734]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-CE-33-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes to supersede Airworthiness Directive 
(AD) 97-14-01, which currently applies to all Pilatus Britten-Norman 
(Pilatus Britten-Norman) Limited 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 right-hand 
rudder bar assembly and the inadvertent omission of requiring 
inspection of the rudder pedal beams prompted this action. This 
proposed AD would retain the requirements of AD 97-14-01 and require 
inspections of the right-hand rudder bar assembly and each rudder pedal 
beam. The actions specified by the proposed 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: The Federal Aviation Administration (FAA) must receive any 
comments on this proposed rule on or before October 25, 2002.

ADDRESSES: Submit comments to FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2002-CE-33-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. You may view any 
comments at this location between 8 a.m. and 4 p.m., Monday through 
Friday, except Federal holidays. You may also send comments 
electronically to the following address: [email protected]. 
Comments sent electronically must contain ``Docket No. 2002-CE-33-AD'' 
in the subject line. If you send comments electronically as attached 
electronic files, the files must be formatted in Microsoft Word 97 for 
Windows or ASCII text.
    You may get service information that applies to this proposed 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 also view this information at the Rules Docket at the address 
above.

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:

Comments Invited

How Do I Comment on This Proposed AD?

    The FAA invites comments on this proposed rule. You may submit 
whatever written data, views, or arguments you choose. You need to 
include the rule's docket number and submit your comments to the 
address specified under the caption ADDRESSES. We will consider all 
comments received on or before the closing date. We may amend this 
proposed rule in light of comments received. Factual information that 
supports your ideas and suggestions is extremely helpful in evaluating 
the effectiveness of this proposed AD action and determining whether we 
need to take additional rulemaking action.

Are There Any Specific Portions of This Proposed AD I Should Pay 
Attention To?

    The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed rule that 
might suggest a need to modify the rule. You may view all comments we 
receive before and after the closing date of the rule in the Rules 
Docket. We will file a report in the Rules Docket that summarizes each 
contact we have with the public that concerns the substantive parts of 
this proposed AD.

How Can I Be Sure FAA Receives My Comment?

    If you want FAA to acknowledge the receipt of your mailed comments, 
you must include a self-addressed, stamped postcard. On the postcard, 
write ``Comments to Docket No. 2002-CE-33-AD.'' We will date stamp and 
mail the postcard back to you.

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 Has Happened Since AD 97-14-01 To Initiate This Action?

    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.

[[Page 58735]]

Is There Service Information That Applies to This Subject?

    B-N Group Ltd. has issued Service Bulletin Number SB 111, Issue 2, 
dated April 1, 2002.

What Are the Provisions of This Service Bulletin?

    The service bulletin includes procedures for:
--Repetitively inspecting the left-hand and right-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 terminating action for the repetitive inspections.

What Action Did the CAA Take?

    The CAA classified this service bulletin as mandatory in order to 
assure the continued airworthiness of these airplanes in the United 
Kingdom. The CAA classifying a service bulletin as mandatory is the 
same in the United Kingdom as the FAA issuing an AD in the United 
States.

Was This in Accordance With the Bilateral Airworthiness Agreement?

    These airplane models are manufactured in the United Kingdom and 
are 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 CAA has 
kept FAA informed of the situation described above.

The FAA's Determination and an Explanation of the Provisions of the 
Proposed AD

What Has FAA Decided?

    The FAA has examined the findings of the CAA; reviewed all 
available information, including the service information referenced 
above; and determined that:
--The unsafe condition referenced in this document exists or could 
develop on other Pilatus Britten-Norman BN-2A and BN2A Mk. III series 
airplanes of the same type design that are on the U.S. registry;
--The actions of AD 97-14-01 should be retained, and the right-hand 
(co-pilot's) rudder bar assembly and the rudder pedal beams should be 
included in the inspection requirements; and
--AD action should be taken in order to correct this unsafe condition.

What Would the Proposed AD Require?

    This proposed AD would 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.

Cost Impact

How Many Airplanes Would the Proposed AD Impact?

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

What Would Be the Cost Impact of the Proposed AD on Owners/Operators of 
the Affected Airplanes?

    We estimate the following costs to accomplish the proposed 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                                         Total cost
                Labor cost                          Parts cost              per           Total cost on U.S.
                                                                          airplane            operators
----------------------------------------------------------------------------------------------------------------
6 workhours x $60 = $360.................  No parts required..........        $360.  $360 x 113 = $40,680
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
replacements that would be required based on the results of the 
proposed inspection. We have no way of determining the number of 
airplanes that may need such replacement:

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

Compliance Time of This Proposed AD

What Would Be the Compliance Time of This Proposed AD?

    The compliance time of this proposed 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 have determined to use 
the number of landings as the compliance time for this proposed 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

Would This Proposed AD Impact Various Entities?

    The regulations proposed herein would 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 proposed rule would not have federalism 
implications under Executive Order 13132.

Would This Proposed 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) if promulgated, 
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 draft regulatory evaluation 
prepared for this action has been placed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 14 
CFR part 39 of the Federal Aviation Regulations as follows:

[[Page 58736]]

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:

Pilatus Britten-Norman Limited: 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 
following airplane models, all serial numbers, that are certificated 
in any category:

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

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

    (2) 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 the effective   Service Bulletin
 rudder pedal beam for         date of this AD and   No. BN-2/SB. 56,
 cracks and replace any        thereafter at         Issue 2, dated
 cracked beam with a P/N NB-   intervals not to      February 13, 1978.
 45-C-2153 (Post Mod No. BB/   exceed 500
 M/341) rudder pedal beam.     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 the effective   Not Applicable.
 C-2153 (Post Mod No. BB/M/    date of this AD.
 341) rudder pedal beams.
------------------------------------------------------------------------


    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

[[Page 58737]]

of compliance or adjust the compliance time if:
    (i) Your alternative method of compliance provides an equivalent 
level of safety; and
    (ii) The Standards Office Manager, 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 Standards Office Manager.
    (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) 29-4059; 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 
Sec.  Sec.  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) How do I get copies of the documents referenced in this AD? 
You may obtain copies of the documents 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 examine these documents at FAA, Central Region, Office of the 
Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.
    (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).


    Issued in Kansas City, Missouri, on September 11, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-23653 Filed 9-17-02; 8:45 am]
BILLING CODE 4910-13-P