[Federal Register Volume 62, Number 203 (Tuesday, October 21, 1997)]
[Rules and Regulations]
[Pages 54575-54576]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-27785]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 86-CE-23-AD; Amendment 39-10171; AD 86-07-02 R1]
RIN 2120-AA64


Airworthiness Directives; Pilatus Britten-Norman Ltd. (Formerly 
Britten-Norman) BN2A MK. 111 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment revises Airworthiness Directive (AD) 86-07-02, 
which currently requires repetitively inspecting the junction of the 
torque link lug and upper case of the main landing gear (MLG) torque 
link assemblies for cracks on Pilatus Britten-Norman Ltd. (Pilatus 
Britten-Norman) BN-2A, BN-2B, BN-2T, and BN2A MK. 111 series airplanes, 
and replacing any part found cracked with a like part. This AD removes 
from the applicability the BN-2A, BN-2B, and BN-2T series airplanes, 
and retains the repetitive inspection and replacement (if necessary) 
requirements of AD 86-07-02 for the BN2A MK. 111 series airplanes. This 
AD results from the Federal Aviation Administration's determination 
that additional AD action needs to be taken on the BN-2A, BN-2B, and 
BN-2T series airplanes. This additional action will be addressed in a 
separate AD. The actions specified by this AD are intended to prevent 
failure of the main landing gear caused by cracks in the torque link 
area, which could lead to loss of control of the airplane during 
landing operations.

DATES: Effective November 28, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 28, 1997.

ADDRESSES: Service information that applies to this AD may be obtained 
from Fairey Hydraulics Limited, Claverham, Bristol, England; or Pilatus 
Britten-Norman Limited, Bembridge, Isle of Wight, United Kingdom PO35 
5PR; telephone 44-1983 872511; facsimile 44-1983 873246. This 
information may also be examined at the Federal Aviation Administration 
(FAA), Central Region, Office of the Regional Counsel, Attention: Rules 
Docket No. 86-CE-23-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, Aerospace 
Engineer, Small Airplane Directorate, Airplane 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 Britten-
Norman BN2A MK. 111 series airplanes was published in the Federal 
Register as a notice of proposed rulemaking on May 27, 1997 (62 FR 
28644). The NPRM proposed to revise AD 86-07-02 by removing the BN-2A, 
BN-2B, and BN-2T series airplanes from the applicability of that AD. 
The NPRM proposed to retain the requirement of repetitively inspecting 
the junction of the torque link lug and upper case of the MLG torque 
link assemblies for the BN2A MK. 111 series airplanes. The FAA is 
issuing a separate AD action for the BN-2A, BN-2B, and BN-2T series 
airplanes to require a modification that, when incorporated, would 
eliminate the repetitive inspection requirement currently required by 
AD 86-07-02. Accomplishment of the proposed inspections as specified in 
the NPRM would be in accordance with Fairey Hydraulics Limited Service 
Bulletin (SB) 32-7, Issue 3, dated January 30, 1990; and Fairey 
Hydraulics Limited SB 32-10, Issue 2, dated November 10, 1992.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed AD 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 AD as proposed except for 
minor editorial corrections. The FAA has

[[Page 54576]]

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 1 workhour per 
airplane to accomplish the initial inspection, and that the average 
labor rate is approximately $60 an hour. Based on these figures, the 
total cost impact of this AD on U.S. operators is estimated to be $540 
or $60 per airplane. This figure only takes into account the cost of 
the initial inspection and does not take into account the cost of any 
repetitive inspections. The FAA has no way of determining the number of 
repetitive inspections each of the owners/operators will incur over the 
life of the affected airplanes.
    In addition, the inspections are currently required by AD 86-07-02 
on the 9 affected airplanes. This AD does not require any additional 
actions over that already required by AD 86-07-02.

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 ``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) 86-07-02, Amendment 39-5382, and by adding a new AD to read as 
follows:

86-07-02 R1  Pilatus Britten-Norman Ltd: Amendment 39-10171; Docket 
No. 86-CE-23-AD. Revises AD 86-07-02, Amendment 39-5382.

    Applicability: Models BN2A MK. 111, BN2A MK. 111-2, and BN2A MK. 
111-3 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 (f) 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.

    Compliance: Required prior to further flight after the effective 
date of this AD (see Note 2) or within 100 hours time-in-service 
(TIS) after the last inspection accomplished in accordance with AD 
86-07-02, whichever occurs later, and thereafter at intervals not to 
exceed 100 hours TIS.

    Note 2: The ``prior to further flight after the effective date 
of this AD'' compliance time was the original initial compliance 
time of AD 86-07-02, and is being retained to provide credit and 
continuity for already-accomplished and future inspections.

    To prevent failure of the main landing gear caused by cracks in 
the torque link assembly area, which could lead to loss of control 
of the airplane during landing operations, accomplish the following:
    (a) Inspect the junction of the torque link lug and upper case 
for cracks (using a 10-power magnifying glass or by dye penetrant 
methods) in accordance with Fairey Hydraulics Limited Service 
Bulletin (SB) 32-7, Issue 3, dated January 30, 1990; or Fairey 
Hydraulics SB 32-10, Issue 2, dated November 10, 1992, as 
applicable. Pilatus Britten-Norman SB BN-2/SB. 173, Issue 3, dated 
November 16, 1990, references Fairey Hydraulic Limited SB 32-7; and 
Pilatus Britten-Norman SB BN-2/SB.209, Issue 1, dated November 30, 
1992, references Fairey Hydraulic Limited SB 32-10.
    (b) If cracked parts are found during any of the inspections 
required by this AD, prior to further flight, replace the cracked 
parts with airworthy parts in accordance with the applicable 
maintenance manual.
    (c) If the landing gear is replaced, only equal pairs of the 
same manufacturer are approved as replacement parts. Mixing of 
different manufacturer landing gears is not authorized.
    (d) The intervals between the repetitive inspections required by 
this AD may be adjusted up to 10 percent of the specified interval 
to allow accomplishing these actions along with other scheduled 
maintenance on the airplane.
    (e) 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 inspection requirements of this AD can be accomplished.
    (f) 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, 1201 Walnut, suite 900, Kansas City, Missouri 64106.
    (1) The request should be forwarded through an appropriate FAA 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Small Airplane Directorate.
    (2) Alternative methods of compliance approved for AD 86-07-02 
are considered approved as alternative methods of compliance for 
this AD.

    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.

    (g) The inspections required by this AD shall be done in 
accordance with Fairey Hydraulics Limited Service Bulletin 32-7, 
Issue 3, dated January 30, 1990, or Fairey Hydraulics Service 
Bulletin 32-10, Issue 2, dated November 10, 1992, as applicable. 
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 from Fairey Hydraulics Limited, 
Claverham, Bristol, England; or 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.
    (h) This amendment (39-10171) revises AD 86-07-02, Amendment 39-
5382.
    (i) This amendment (39-10171) becomes effective on November 28, 
1997.

    Issued in Kansas City, Missouri, on October 14, 1997.
Mary Ellen Schutt,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-27785 Filed 10-20-97; 8:45 am]
BILLING CODE 4910-13-U