[Federal Register: December 11, 2002 (Volume 67, Number 238)]
[Rules and Regulations]
[Page 76106-76109]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11de02-2]
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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
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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):
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If Then When
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(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.
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(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:
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Action Compliance Procedures
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(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).
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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]
BILLING CODE 4910-13-P