AD 2002-22-03
Recurring
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Pilatus Aircraft Limited | PC-7 | Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7 Airplanes |
Unsafe Condition
Cracks in the main landing gear front attachment brackets could result in failure of the brackets. Such failure could lead to the main landing gear leg detaching from the wing main spar.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Repetitively inspect the main landing gear front attachment brackets for cracks using the Impedance-Plane Eddy-Current Inspection. If cracks are found, install improved-design brackets. Installing the improved-design brackets terminates the required inspections.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 90 days after December 20, 2002 (the effective date of this AD).
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
PILATUS Aircraft Ltd. Model PC-7 airplanes, serial numbers 101 through 618, that are certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
This amendment adopts a new airworthiness directive (AD) that applies to certain PILATUS Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires you to repetitively inspect the main landing gear front attachment brackets for cracks, and, if cracks are found, install improved-design brackets. Installing the improved-design brackets terminates the required inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to detect and correct cracks in the main landing gear front attachment brackets, which could result in failure of the brackets. Such failure could lead to the main landing gear leg detaching from the wing main spar.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 67, Number 212 (Friday, November 1, 2002)]
[Rules and Regulations]
[Pages 66541-66544]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-27418]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-CE-28-AD; Amendment 39-12927; AD 2002-22-03]
RIN 2120-AA64
Airworthiness Directives; PILATUS Aircraft Ltd. Model PC-7
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to certain PILATUS Aircraft Ltd. (Pilatus) Model PC-7
airplanes. This AD requires you to repetitively inspect the main
landing gear front attachment brackets for cracks, and, if cracks are
found, install improved-design brackets. Installing the improved-design
brackets terminates the required inspections. This AD is the result of
mandatory continuing airworthiness information (MCAI) issued by the
airworthiness authority for Switzerland. The actions specified by this
AD are intended to detect and correct cracks in the main landing gear
front attachment brackets,
[[Page 66542]]
which could result in failure of the brackets. Such failure could lead
to the main landing gear leg detaching from the wing main spar.
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 Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224;
or from Pilatus Business Aircraft Ltd., Product Support Department,
11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-
9099; facsimile: (303) 465-6040. You may view this information at the
Federal Aviation Administration (FAA), Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2002-CE-28-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 Federal Office for Civil Aviation (FOCA), which is the
airworthiness authority for Switzerland, recently notified FAA that an
unsafe condition may exist on certain Pilatus Model PC-7 airplanes. The
FOCA reports that an operator of a similar aircraft type design, which
uses identical main landing gear support brackets, reported a single
crack in one bracket. A fleet inspection of the operator's aircraft
revealed stress corrosion cracking in more than 20 aircraft.
What Is the Potential Impact if FAA Took No Action?
Cracks in the main landing gear front attachment brackets could
result in failure of the brackets. Such failure could lead to the main
landing gear leg detaching from the wing main spar.
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
certain Pilatus Model PC-7 airplanes. This proposal was published in
the Federal Register as a notice of proposed rulemaking (NPRM) on
August 9, 2002 (67 FR 51794). The NPRM proposed to repetitively inspect
the main landing gear front attachment brackets for cracks, and, if
cracks are found, install improved-design brackets. Installing the
improved-design brackets terminates the required inspections.
Was the Public Invited To Comment?
The FAA encouraged interested persons to participate in the making
of this amendment. We did not receive any 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 14 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:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operator
----------------------------------------------------------------------------------------------------------------
4 workhours x $60 = $240............ No parts required..... $240 $240 x 14 = $3,360.
----------------------------------------------------------------------------------------------------------------
The FAA has no method of determining the number of repetitive
inspections each owner/operator would incur over the life of each of
the affected airplanes so the cost impact is based on the initial
inspection.
We estimate the following costs to accomplish any necessary
replacements that would be required based on the results of the
inspection. We have no way of determining the number of airplanes that
may need such replacement:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
80 workhours x $60 = $4,800 $2,500 per side.. $4,800 + $2,500 =
per side. $7,300 per side.
------------------------------------------------------------------------
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 evaluation prepared for this
action is contained in the Rules Docket. A copy
[[Page 66543]]
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:
2002-22-03 Pilatus Aircraft LTD.: Amendment 39-12927; Docket No.
2002-CE-28-AD.
(a) What airplanes are affected by this AD? This AD affects
Model PC-7 airplanes, serial numbers 101 through 618, that are
certificated in any category.
(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 main
landing gear front attachment brackets, which could result in
failure of the brackets. Such failure could lead to the main landing
gear leg detaching from the wing main spar.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
------------------------------------------------------------------------
Compliance Actions Procedures
------------------------------------------------------------------------
(1) Initial Inspection: At Inspect, using the In accordance with
whichever of the following Impedance-Plane the ACCOMPLISHMENT
occurs later, unless Eddy-Current INSTRUCTIONS
already accomplished: (i) Inspection, both section of Pilatus
Upon the accumulation of main landing gear PC-7 Service
3,000 hours time-in-service front attachment Bulletin No. 57-
(TIS) on the attachment brackets, part 004, Revision No.
brackets or 10 years after number (P/N) 1, dated June 17,
installation of the 111.34.07.105 and P/ 2002; the
brackets, whichever occurs N 111.34.07.106 for ACCOMPLISHMENT
first; or (ii) within 90 cracks. INSTRUCTIONS
days after December 20, section of Pilatus
2002 (the effective date of PC-7 Service
this AD). Bulletin No. 57-
005, dated
September 10, 2001;
and Pilatus PC-7
Maintenance Manual,
Temporary Revision
No. 05-10, dated
September 10, 2001.
-----------------------------
(2) Repetitive Inspections: Inspection, using In accordance with
Within 12 calendar months the Impedance-Plane the ACCOMPLISHMENT
after the initial Eddy-Current INSTRUCTIONS
inspection required in Inspection, both section of Pilatus
paragraph (d)(1) of this AD main landing gear PC-7 Service
and thereafter at intervals front attachment Bulletin No. 57-
not to exceed 12 calendar brackets, P/N 004, Revision No.
months. 111.34.07.105 and P/ 1, dated June 17,
N 111.34.07.106 for 2002; the
cracks. ACCOMPLISHMENT
INSTRUCTIONS
section of Pilatus
PC-7 Service
Bulletin No. 57-
005, dated
September 10, 2001;
and Pilatus PC-7
Maintenance Manual,
Temporary Revision
No. 05-10, dated
September 10, 2001.
-----------------------------
(3) Prior to further flight If a crack is found In accordance with
after the inspection in in any main landing the ACCOMPLISHMENT
which the damage was found. gear front INSTRUCTIONS
attachment bracket section of Pilatus
during any PC-7 Service
inspection required Bulletin No. 57-
in this AD, replace 005, dated
with an improved September 10, 2001.
bracket, P/N
557.10.09.045, P/N
557.10.09.046, or
FAA-approved
equivalent P/N.
Repetitive
inspections are
still required on
any P/N
111.34.07.105 and P/
N 111.34.07.106 for
cracks.
-----------------------------
(4) At any time as You may terminate In accordance with
terminating action for the the inspections the ACCOMPLISHMENT
repetitive inspections. required in INSTRUCTIONS
However, you must replace paragraphs (d)(1) section of Pilatus
prior to further flight if and (d)(2) of this PC-7 Service
you find cracks during any AD when improved Bulletin No. 57-
inspections required by design main landing 005, dated
this AD. gear front September 10, 2001.
attachment
brackets, P/N
557.10.09.045, P/N
557.10.09.046, or
FAA-approved
equivalent P/Ns,
are installed on
both sides of the
airplane.
-----------------------------
(5) As of December 20, 2002 Only install main Not Applicable.
(the effective date of this landing gear
AD). brackets that are P/
N 557.10.09.045, P/
N 557.10.09.046, or
FAA-approved
equivalent P/Ns.
------------------------------------------------------------------------
Note 1: If you find cracks on one side only, you are only
required to replace the damaged side with the new improved-design
bracket and continue the repetitive inspections required by
paragraph (d)(2) of this AD. Repetitive inspections are still
required on any installed bracket with either P/N 111.34.07.105 or
P/N 111.34.07.106.
(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 2: 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
[[Page 66544]]
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 PC-7 Service Bulletin No. 57-004, Revision No. 1, dated
June 17, 2002; Pilatus PC-7 Service Bulletin No. 57-005, dated
September 10, 2001; and Pilatus PC-7 Maintenance Manual, Temporary
Revision No. 05-10, dated September 10, 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 Pilatus
Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland;
telephone: +41 41 619 63 19; facsimile: +41 41 619 6224; or from
Pilatus Business Aircraft Ltd., Product Support Department, 11755
Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-9099;
facsimile: (303) 465-6040. 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 3: The subject of this AD is addressed in Swiss AD HB 2002-
270, dated June 24, 2002.
(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. 02-27418 Filed 10-31-02; 8:45 am]
BILLING CODE 4910-13-P
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
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