[Federal Register Volume 62, Number 46 (Monday, March 10, 1997)]
[Proposed Rules]
[Pages 10756-10758]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-5840]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 84-CE-18-AD]
RIN 2120-AA64
Airworthiness Directives; Pilatus Britten-Norman Ltd. BN-2, BN-
2A, BN-2B, BN-2T, and BN-2A Mk 111 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to revise 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) BN-2, BN-2A, BN-
2B, BN-2T, and BN-2A Mk 111 series airplanes, and replacing any
cracked, worn, or ill-fitting part. The proposed action would retain
the same action required in AD 84-23-06, except the action would only
be applicable to the BN-2A Mk 111 series airplanes. The proposed action
is prompted by a terminating modification only applicable to the
Pilatus BN-2, BN-2A, BN-2B, BN-2T series airplanes that would remove
them from the applicability of AD 84-23-06. The actions specified by
the proposed 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: Comments must be received on or before May 12, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 84-CE-18-AD, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106. Comments may be inspected at
this location between 8 a.m. and 4 p.m., Monday through Friday,
holidays excepted.
Service information that applies to the proposed AD may be obtained
from Pilatus Britten-Norman Limited, Bembridge, Isle of Wight, United
Kingdom PO35 5PR; telephone 44-1983 872511; facsimile 44-1983 873246.
This information also may be examined at the Rules Docket at the
address above.
FOR FURTHER INFORMATION CONTACT:
Mr. Tom Rodriguez, Program Officer, Brussels Aircraft Certification
Division, FAA, Europe, Africa, and Middle East Office, c/o American
Embassy, b-1000 Brussels, Belgium; telephone (322) 508-2715; facsimile
(322) 230-6899;
or
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:
Comments Invited
Interested persons are invited to participate in the making of the
[[Page 10757]]
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 84-CE-18-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 84-CE-18-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The Civil Airworthiness Authority (CAA), which is the airworthiness
authority for the United Kingdom (UK), notified the FAA that an unsafe
condition may exist on certain Pilatus BN-2A Mk 111 series airplanes.
The CAA reports that several incidents have revealed cracking, wear,
and ill-fitting parts in the upper wing mount brackets on the wing
mounted engines which could eventually result in structural failure of
the wing. This condition, if not detected and corrected, could result
in failure of the engine mounting brackets of the wing mounted engines
and possible structural failure and loss of control of the airplane.
Pilatus has issued service bulletin BN-2/SB.61, Issue 5, dated December
9, 1981, which specifies inspecting for cracked, worn, or ill-fitting
parts, and if found, repair and continue to repetitively inspect.
This service bulletin is also referenced in AD 84-23-06. The
proposed action would be a revision to AD 84-23-06 to remove the
Pilatus BN-2, BN-2A, BN-2B and BN-2T series airplanes from the
applicability of AD 84-23-06. Since publication of this AD, a
modification terminating the repetitive inspections became available to
the Pilatus BN-2, BN-2A, BN-2B and BN-2T series airplanes that is not
applicable to the BN-2A Mk 111 series airplanes. The terminating
modification is proposed in a Notice for Proposed Rulemaking (NPRM)
Docket No. 96-CE-17-AD. The Pilatus Service Bulletin (SB) BN-2/SB.61,
Issue 5, dated December 9, 1981, is also referenced in this NPRM for
the terminating action applicable to the Pilatus BN-2, BN-2A, BN-2B and
BN-2T series airplanes.
The UK CAA classified this service bulletin as mandatory and issued
AD No. 0619 in order to assure the continued airworthiness of these
airplanes in the United Kingdom.
This airplane model is manufactured in the United Kingdom and is
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 UK CAA has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the UK CAA, reviewed all available information, and
determined that AD action is necessary for products of this type design
that are certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop in other Pilatus BN-2A Mk 111 series airplanes of the
same type design registered for operation in the United States, the
proposed AD would revise AD 84-23-06 to eliminate Pilatus BN-2, BN-2A,
BN-2B, BN-2T series airplanes from the applicability of this AD and
would retain the Pilatus BN-2A Mk 111 series airplanes in the
applicability section of the proposed AD, and would also retain the
requirement for:
(1) Visually inspecting the upper engine to wing mounting brackets
for minimum lug bolt hole-to-edge distance (0.2625 inches),
(2) Inspecting for elongation of the bolt holes, distortion,
delamination, cracks, flaking, and corrosion, and
(3) Inspecting the bolts for correct bearing length, and loose and
fretted bushings.
If the lug bolt hole-to-edge distance is less than the specified
minimum, prior to further flight, correct the defects. If the bolt
holes are elongated, or if any bushings are loose or fretted, modify
and correct. 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). If any lug is
distorted or delaminated, replace the deficient part. If any part is
corroded or flaking, replace the part. If any of the bolts are of
incorrect length or damaged, replace with new units of the correct
length and continue to repetitively inspect.
Cost Impact
The FAA estimates that 9 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 2
workhours per airplane to accomplish the proposed 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 the proposed AD on U.S.
operators is estimated to be $1,080 or $120 per airplane. This figure
is based on the proposed initial inspection cost and does not include
workhours for repetitive inspections. The FAA has no way to determine
how many of these airplanes have already accomplished this action.
Regulatory Impact
The regulations proposed herein would 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
proposal would 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 ``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.
[[Page 10758]]
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Pilatus Britten-Norman Ltd.: Docket No. 84-CE-18-AD; Revises AD 84-
23-06, Amendment 39-4942.
Applicability: BN-2T 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,
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 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 the following areas:
(1) The upper engine to wing mounting brackets for:
(i) Minimum lug bolt hole-to-edge distance (0.2625 inches),
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, 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 with paragraph 1 of 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, Brussels Aircraft
Certification Division, FAA, Europe, Africa, and Middle East Office,
c/o American Embassy, B-1000 Brussels, Belgium; telephone (322)
508.2715; facsimile(322) 230.6899; or Mr. S. M. Nagarajan, Project
Officer, 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,
Brussels Aircraft Certification Office or 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 Brussels Aircraft Certification Division or the
Small Airplane Directorate.
(e) All persons affected by this directive may obtain copies of
the document referred to herein upon request to Pilatus Britten-
Norman Limited, Bembridge, Isle of Wight, United Kingdom PO35 5PR;
telephone 44-1983 872511; facsimile 44-1983 873246; or may examine
this document at the FAA, Central Region, Office of the Assistant
Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri
64106.
Issued in Kansas City, Missouri, on February 28, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-5840 Filed 3-7-97; 8:45 am]
BILLING CODE 4910-13-U
