[Federal Register Volume 62, Number 205 (Thursday, October 23, 1997)]
[Rules and Regulations]
[Pages 55156-55157]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-27931]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 84-CE-18-AD; Amendment 39-10172; AD 84-23-06 R1]
RIN 2120-AA64
Airworthiness Directives; Pilatus Britten-Norman Ltd. Models BN-
2, BN-2A, BN-2B, BN-2T, and BN-2A MK. 111 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment revises airworthiness directive (AD) 84-23-06,
which currently requires repetitively inspecting the upper mounting
brackets, bolts, and bushings on wing mounted engines for cracks, wear,
and insufficient fit on certain Pilatus Britten-Norman Ltd. (Pilatus)
Models BN-2, BN-2A, BN-2B, BN-2T, and BN-2A MK. 111 series airplanes,
and replacing any cracked, worn, or ill-fitting part. This action
retains the same action required in AD 84-23-06, except the action is
only applicable to the BN-2A MK. 111 series airplanes. This action is
the result of a terminating modification, now available to the Pilatus
Models BN-2, BN-2A, BN-2B, BN-2T airplanes, which removes them from the
applicability of AD 84-23-06. The actions specified by this AD are
intended to prevent failure of the upper mounting brackets on wing
mounted engines, which could possibly cause structural failure of the
airplane.
DATES: Effective November 24, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 24, 1997.
ADDRESSES: Service information that applies to this AD may be obtained
from Pilatus Britten-Norman Limited, Bembridge, Isle of Wight, United
Kingdom PO35 5PR; telephone 44-19-83-872511; facsimile 44-19-83-873246.
This information may also be examined at the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket 84-CE-18-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: Mr. S. M. Nagarajan, Project Officer,
Small Airplane Directorate, Aircraft Certification Service, FAA, 1201
Walnut, suite 900, Kansas City, Missouri 64106; telephone (816) 426-
6932; facsimile (816) 426-2169.
SUPPLEMENTARY INFORMATION:
Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to include an AD that would apply to Pilatus BN-2, BN-2A,
BN-2B, BN-2T, and BN-2A MK. 111 series was published in the Federal
Register on March 10, 1997 (62 FR 10756). The proposed AD would revise
AD 84-23-06 by deleting the Pilatus BN-2, BN-2A, BN-2B, BN-2T series
airplanes from the AD, and by retaining the following for the Pilatus
BN-2A MK. 111 series airplanes:
(1) Visually inspecting the upper engine mounting bracket lugs for
cracks extending radially from the bolt holes in the doubler;
(2) Inspecting for elongation of the bolt holes, distortion,
delamination, cracks, flaking, and corrosion;
(3) Inspecting the bolts for correct bearing length, and loose and
fretted bushings; and
(4) Correcting any discrepancies found.
Accomplishment of this action will be in accordance with Pilatus
Britten-Norman Ltd. Service Bulletin (SB) BN-2/SB.61, Issue 5, dated
December 9, 1981, which is also referenced in the Notice of Proposed
Rulemaking (NPRM) Docket 96-CE-17-AD for a terminating action
applicable to the Pilatus BN-2, BN-2A, BN-2B and BN-2T series
airplanes.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
The FAA's Determination
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. The FAA has determined that these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
Cost Impact
The FAA estimates that 9 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 2 workhours per
airplane to accomplish this action and the average labor rate is
approximately $60 an hour. There are no parts required for the initial
inspection. Based on these figures, the total cost impact for the
initial inspection of this AD on U.S. operators is estimated to be
$1,080 or $120 per airplane. This figure is based on the initial
inspection cost and does not include workhours for repetitive
inspections because the FAA does not have the information to determine
the number of repetitive inspections that would be incurred over the
life of the airplane.
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
[[Page 55157]]
``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 removing Airworthiness Directive
(AD) 84-23-06, Amendment 39-4942, (49 FR 43621, October 31, 1984), and
adding a new AD to read as follows:
84-23-06 R1. Pilatus Britten-Norman LTD.: Amendment 39-10172;
Docket No. 84-CE-18-AD; Revises AD 84-23-06, Amendment 39-4942.
Applicability: BN-2A MK. 111 Series 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.
Note 2: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 2 and Level 3 structures are designations of the Level 1
paragraph they immediately follow.
Compliance: Required initially upon the accumulation of 500
hours time-in-service (TIS) or within the next 50 hours TIS after
the effective date of this AD, whichever occurs later, unless
already accomplished (compliance with AD 84-23-06), and thereafter
at intervals not to exceed 500 hours TIS.
To prevent failure of the upper mounting brackets on both wing
mounted engines, which could possibly cause structural failure of
the airplane, accomplish the following:
(a) Visually inspect the following areas in accordance with
paragraphs 1 through 6 of the ``Inspection'' section of the Pilatus
Britten-Norman (Pilatus) Service Bulletin (SB) No. BN-2/SB.61, Issue
5, dated December 9, 1981:
(1) The upper engine to wing mounting brackets for:
(i) Minimum lug bolt hole-to-edge distance, elongation of the
bolt holes, distortion, delamination, cracks, flaking, and
corrosion;
(ii) The bolts for correct bearing length; and
(iii) Loose and fretted bushings.
(2) Prior to further flight, correct defects in accordance with
the following:
(i) If the lug bolt hole-to-edge distance is less than the
specified minimum (0.2625-inches), correct in accordance with
paragraph 3 of the ``Rectification/Modification'' section of Pilatus
SB No. BN-2/SB.61, Issue 5, dated December 9, 1981;
(ii) If the bolt holes are elongated, or if any bushings are
loose or fretted, modify and correct in accordance with paragraph 4
of the ``Rectification/Modification'' section of Pilatus SB No. BN-
2/SB.61, Issue 5, dated December 9, 1981;
(iii) If any mounting bracket is cracked, modify both brackets
on the same engine installation (left side engine or right side
engine) concurrently (even if only one bracket is defective) in
accordance with paragraph 1 of the ``Rectification/Modification''
section of Pilatus SB No. BN-2/SB.61, Issue 5, dated December 9,
1981;
(iv) If any lug is distorted or delaminated, replace the
deficient part in accordance with paragraphs 1 and 2 of the
``Rectification/Modification'' section of Pilatus SB No. BN-2/SB.61,
Issue 5, dated December 9, 1981;
(v) If any inspected part is corroded or flaking, replace the
part in accordance paragraph 1 with the ``Rectification/
Modification'' section of Pilatus SB No. BN-2/SB.61, Issue 5, dated
December 9, 1981; and
(vi) If any of the bolts are of incorrect length or damaged,
replace with new units of the correct length in accordance with
paragraphs 1 and 2 of the ``Rectification/Modification'' section of
Pilatus SB No. BN-2/SB.61, Issue 5, dated December 9, 1981.
(b) The intervals between the repetitive inspections required by
this AD may be adjusted up to 10 percent of the specified interval
to allow for accomplishing these inspections concurrent with the
other scheduled maintenance of the airplane.
(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, FAA, 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(e) The inspections, modifications, and replacements, required
by this AD shall be done in accordance with Pilatus Britten-Norman
Service Bulletin No. BN-2/SB.61, Issue: 5, Date: December 9, 1981.
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 Pilatus Britten-Norman Limited,
Bembridge, Isle of Wight, United Kingdom PO35 5PR. 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 Capitol Street, NW.,
suite 700, Washington, DC.
(f) This amendment (39-10172) becomes effective on November 24,
1997.
Issued in Kansas City, Missouri, on October 16, 1997.
Mary Ellen A. Schutt,
Acting Manger, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-27931 Filed 10-22-97; 8:45 am]
BILLING CODE 4910-13-P
