[Federal Register Volume 67, Number 212 (Friday, November 1, 2002)]
[Rules and Regulations]
[Pages 66544-66546]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-27419]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-CE-21-AD; Amendment 39-12926; AD 2002-22-02]
RIN 2120-AA64
Airworthiness Directives; Pilatus Britten-Norman Limited BN-2,
BN-2A, BN-2B, BN-2T, and BN2A MK. III Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to all Pilatus Britten-Norman Limited (Pilatus Britten-Norman)
BN-2, BN-2A, BN-2B, BN-2T, and BN2A MK. III series airplanes. This AD
requires you to repetitively inspect the bottom corner of the engine
mount bracket for cracks and replace any cracked bracket with a new
one. This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for the United
Kingdom. The actions specified by this AD are intended to detect and
correct cracks in the engine mount bracket. Such a condition could
cause the engine mount assembly to fail, which could result in the
engine separating from the airplane and lead to loss of control of the
airplane.
DATES: This AD becomes effective on December 20, 2002.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the regulations as of
December 20, 2002.
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-21-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
What Events Have Caused This AD?
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, recently notified FAA that an unsafe
condition may exist on all Pilatus Britten-Norman BN-2, BN-2A, BN-2B,
BN-2T, and BN2A MK. III series airplanes. The CAA reports two
occurrences of extensive cracks being found on the bottom corner of the
engine mount bracket between the attachment flange and the main
bracket. The cracks were found during regular scheduled maintenance.
The manufacturer has determined that this condition is a result of
the reinforcing doubler being too close to the flange.
What Is the Potential Impact if FAA Took No Action?
This condition, if not detected and corrected, could result in
failure of the engine mount. Such failure could result in the engine
separating from the airplane and lead to loss of control of the
airplane.
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-2, BN-2A, BN-2B, BN-2T, and BN2A MK. III
series airplanes. This proposal was published in the Federal Register
as a notice of proposed rulemaking (NPRM) on August 22, 2002 (67 FR
54384). The NPRM proposed to require you to repetitively inspect the
bottom corner of the engine mount bracket for cracks, replace any
cracked bracket, return the removed bracket(s) to Pilatus Britten-
Norman, and report the return to FAA.
Are There Differences Between This AD, the Service Information, and the
CAA AD?
The CAA AD and the service information allow continued flight if
cracks are found in the engine mount bracket that do not exceed certain
limits. The applicable service bulletin specifies replacement of the
engine mount bracket only if cracks are found exceeding this limit, as
does CAA AD 005-11-2001. This AD does not allow continued flight if any
crack is found. FAA policy is to disallow airplane operation when known
cracks exist in primary structure, unless the ability to sustain
ultimate load with these cracks is proven. The engine mount bracket is
considered primary structure, and the FAA has not received any analysis
to prove that ultimate load can be sustained with cracks in this area.
Is There a Modification I Can Incorporate Instead of Repetitively
Inspecting the Engine Mount Brackets?
The FAA has determined that long-term continued operational safety
will be better assured by design changes that remove the source of the
problem rather than by performing repetitive inspections. With this in
mind, we will continue to work with Pilatus Britten-Norman in
collecting information to determine whether a future design change may
be necessary.
Was the Public Invited To Comment?
The FAA encouraged interested persons to participate in the making
of this amendment. We did not receive any
[[Page 66545]]
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 126 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 for
BN-2, BN-2A, BN-2B, and BN2A MK. III series airplanes:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
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4 workhours x $60 per hour = $240....... $10 $250
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We estimate the following costs to accomplish the inspection for
BN-2T series airplanes:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
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8 workhours x $60 per hour = $480....... $10 $490
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We estimate the following costs to accomplish any necessary
replacements for BN-2, BN-2A, BN-2B, and BN-2T series airplanes 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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Parts cost per
Labor cost bracket Total cost per bracket
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48 workhours x $60 per hour = $1,295 $2,880 + $1,295 =
$2,880 per bracket (2 brackets $4,175.
per engine, 2 engines per
airplane).
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We estimate the following costs to accomplish any necessary
replacements for BN2A MK. III series airplanes 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:
------------------------------------------------------------------------
Parts cost per
Labor cost bracket Total cost per bracket
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48 workhours x $60 per hour = $714 $2,880 + $714 =
$2,880 per bracket (2 brackets $3,594.
per engine, 2 engines per
airplane).
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What Is the Compliance Time of This AD?
The compliance time of this AD is ``within the next 500 hours time-
in-service (TIS) or within the next 24 calendar months after the
effective date of this AD, whichever occurs first.''
Why Is The Compliance Time of This AD Presented in Both Hours TIS and
Calendar Time?
We have established the compliance time of this AD in both hours
TIS and calendar time. The unsafe condition is dependent upon
repetitive airplane operation. However, the recommended maintenance
program specifies other actions in this area at intervals not to exceed
2 years. Therefore, the compliance time will ensure that high-time
airplanes are inspected within a certain amount of hours TIS and the
lower time airplanes would be inspected at the next maintenance event
in the affected area. We have determined that this compliance time:
--Will ensure that the unsafe condition is addressed in a timely manner
on all affected airplanes; and
--Will not inadvertently ground any of the affected airplanes.
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
[[Page 66546]]
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 adding a new AD to read as follows:
2002-22-02 Pilatus Britten-Norman Limited: Amendment 39-12926;
Docket No. 2002-CE-21-AD.
(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-2, 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, BN-2B-20, BN-2B-21, BN-2B-26, BN-
2B-27, BN-2T, BN-2T-4R, BN2A MK. III, BN2A MK. III-2, 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 detect and correct cracks in the engine
mount bracket. Such a condition could cause the engine mount
assembly to fail, which could result in the engine separating from
the airplane and lead to loss of control of the airplane.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
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Actions Compliance Procedures
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(1) Inspect the bottom Initially inspect In accordance with
corner of the engine mount within the next 500 Pilatus Britten
bracket between the hours time-in- Norman Service
attachment flange and the service (TIS) or Bulletin SB 275,
main part of the bracket within the next 24 Issue 1, dated
for cracks: (i) If cracks calendar months November 30, 2001.
are found during any after December 20,
inspections, replace the 2002 (the effective
bracket with a new bracket date of this AD),
and continue with the whichever occurs
repetitive inspection first, and
requirements of this AD; repetitively
(ii) If no cracks are found inspect thereafter
during any inspection, at intervals not-to-
continue with the exceed 500 hours
repetitive inspection TIS or 1,000
requirements of this AD. landings, whichever
occurs first.
Replace cracked
bracket prior to
further flight
after the
inspection in which
the crack is found.
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(2) Send the removed Within 10 days after Send the removed
brackets to the Engineering removing the brackets to B-N
and Design Authority, B-N bracket or within Group Limited,
Group Ltd. and report the 10 days after Bembridge, Isle of
return to FAA. The Office December 20, 2002 Wight, United
of Management and Budget (the effective date Kingdom P035 5PR,
(OMB) approved the of this AD), and report the
information collection whichever occurs return to Doug
requirements contained in later. Rudolph, FAA, at
this regulation under the the address in
provisions of the Paperwork paragraph (f) of
Reduction Act of 1980 (44 this AD.
U.S.C. 3501 et seq.) and
assigned OMB Control Number
2120-0056.
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(e) Can I comply with this AD in any other way? You may use an
alternative method of compliance or adjust the compliance time if:
(1) Your alternative method of compliance provides an equivalent
level of safety; and
(2) 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.
Note 1: 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
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) Are any service bulletins incorporated into this AD by
reference? Actions required by this AD must be done in accordance
with Pilatus Britten Norman Service Bulletin SB 275, Issue 1, dated
November 30, 2001. 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.
Note 2: The subject of this AD is addressed in the United
Kingdom CAA-AD Number 005-11-2001, not dated.
(i) When does this amendment become effective? This amendment
becomes effective on December 20, 2002.
Issued in Kansas City, Missouri, on October 22, 2002.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-27419 Filed 10-31-02; 8:45 am]
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