[Federal Register Volume 62, Number 49 (Thursday, March 13, 1997)]
[Rules and Regulations]
[Pages 11763-11764]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-6256]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 92-CE-25-AD; Amendment 39-9962; AD 97-06-05]
RIN 2120-AA64
Airworthiness Directives; Avions Pierre Robin Model R2160
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 Avions Pierre Robin Model R2160 airplanes. This action
requires repetitively inspecting the weld area between the strut and
the lower plate of the nose landing gear leg for cracks, and replacing
the strut when cracks are found. The AD is the result of several
reports of cracks in the weld securing the nose wheel steering bottom
bracket to the nose landing gear leg on the affected airplanes. The
actions specified by this AD are intended to prevent nose landing gear
failure caused by cracks in the weld area between the strut and the
lower plate of the nose landing gear leg, which could result in loss of
control of the airplane during landing operations.
DATES: Effective May 16, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 16, 1997.
ADDRESSES: Service information that applies to this AD may be obtained
from Avions Pierre Robin, 1, Route de Troyes, 21121 Darois France;
telephone: 80 35 61 01; facsimile: 80 35 60 80. This information may
also be examined at the Federal Aviation Administration (FAA), Central
Region, Office of the Assistant Chief Counsel, Attention: Rules Docket
No. 92-CE-25-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. Greg Holt, Program Manager,
Brussels Aircraft Certification Division, FAA, Europe, Africa, and
Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium;
telephone (32 2) 513.2692; facsimile (32 2) 230.6899; or Mr. Roman T.
Gabrys, Project Officer, Small Airplane Directorate, Aircraft
Certification Office, FAA, 1201 Walnut, suite 900, Kansas City,
Missouri 64106; telephone (816) 426-6934; 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 Avions Pierre Robin
Model R2160 airplanes was published in the Federal Register as a notice
of proposed rulemaking (NPRM) on November 13, 1996 (61 FR 58145). The
NPRM proposed to require repetitively inspecting the weld area between
the strut and the lower plate of the nose landing gear leg for cracks,
and replacing the strut when cracks are found. Accomplishment of the
proposed inspections as specified in the NPRM would be in accordance
with Avions Pierre Robin Service Bulletin (SB) No. 101, Revision 3,
dated March 5, 1992.
The NPRM resulted from several reports of cracks in the weld
securing the nose wheel steering bottom bracket to the nose landing
gear leg on the affected airplanes.
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 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.
Differences Between This AD, Service Bulletin, and DGAC AD
Both Avions Pierre Robin SB No. 101, Revision 3, dated March 5,
1992, and DGAC AD 83-206(A)R3, dated March 18, 1992, specify repetitive
inspection intervals of 25 hours time-in-service if a crack in the weld
area is found that is within a certain limit. The limit is ``if the
crack runs along the circumference and is less than 15 mm long max. or/
and radial crack is less than 8 mm max.'' 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 abililty to sustain ultimate load with these cracks is proven. The
nose landing gear leg 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.
Cost Impact
The FAA estimates that 10 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 the AD on U.S. operators is estimated to be $600.
This figure does not take into account the number of repetitive
inspections each airplane owner/operator will incur over the life of
the airplane, or the number of airplanes that could have cracked weld
areas and would need the strut replaced. The FAA has no way of
determining the number of repetitive inspections each owner/operator
would incur over the life of the airplane or the number of nose landing
gear leg struts that could need to be replaced because of cracks in the
weld area.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the
[[Page 11764]]
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 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
97-06-05 Avions Pierre Robin: Amendment 39-9962; Docket No. 92-CE-
25-AD.
Applicability: Model R2160 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.
Compliance: Required initially within the next 100 hours time-
in-service (TIS) after the effective date of this AD, unless already
accomplished, and thereafter as follows, as applicable:
1. If the width of the lower plate of the bottom bracket of the
nose landing gear leg is 84 millimeters: at intervals not to exceed
500 hours TIS; or
2. If the width of the lower plate of the bottom bracket of the
nose landing gear leg is less than 84 millimeters: at intervals not
to exceed 100 hours TIS.
To prevent nose landing gear failure caused by cracks in the
weld area between the strut and the lower plate of the nose landing
gear leg, which could result in loss of control of the airplane
during landing operations, accomplish the following:
(a) Inspect, using dye penetrant methods, the weld area between
the strut and the lower plate of the nose landing gear leg for
cracks in accordance with Avions Pierre Robin Service Bulletin (SB)
No. 101, Revision 3, dated March 5, 1992.
(b) If any crack is found during any inspection required by this
AD, prior to further flight, replace the strut with a new or
serviceable strut.
(1) If the replacement strut is not new, prior to further flight
after installing the strut, accomplish the inspection specified in
paragraph (a) of this AD.
(2) Replacing the strut with a new or serviceable strut does not
eliminate the repetitive inspection requirement of this AD.
(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. 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 Division.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Brussels Aircraft Certification Division.
(e) The inspection required by this AD shall be done in
accordance with Avions Pierre Robin Service Bulletin No. 101,
Revision 3, dated March 5, 1992. 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
Avions Pierre Robin, 1, Route de Troyes, 21121 Darois France. Copies
may be inspected at the FAA, Central Region, Office of the Assistant
Chief 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 (39-9962) becomes effective on May 16, 1997.
Issued in Kansas City, Missouri, on March 6, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-6256 Filed 3-12-97; 8:45 am]
BILLING CODE 4910-13-P