Airworthiness directives: Pilatus Aircraft Ltd.,
[Federal Register: May 9, 2006 (Volume 71, Number 89)]
[Proposed Rules]
[Page 26891-26894]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09my06-25]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-6, PC- 6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
[[Page 26892]]
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2003-09- 01, which applies to Pilatus Aircraft Ltd (Pilatus) Model PC-6 airplanes, all manufacturer serial numbers (MSN) up to and including 939. AD 2003-09-01 currently requires you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations. Since we issued AD 2003-09-01, the FAA determined the action should also apply to all the models of the PC-6 airplanes listed in the type certification data sheet of Type Certificate (TC) No. 7A15 that are produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 2003-09-01 was to all the affected serial numbers of the airplane models listed in TC No. 7A15. Consequently, this proposed AD would retain all the actions of AD 2003-09-01, would add those Fairchild Republic Company airplanes to the applicability of this proposed AD, and would list out the individual specific airplane models. We are proposing this AD to detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight.
DATES: We must receive comments on this proposed AD by June 9, 2006.
ADDRESSES: Use one of the following addresses to comment on this proposed AD:
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224.
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:
Comments Invited
We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ``FAA- 2006-24092; Directorate Identifier 2006-CE-18-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov , including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we receive concerning this proposed AD.
Discussion
Mandatory continuing airworthiness information and the FAA's determination that an unsafe condition existed on a Pilatus Model PC-6 airplane caused us to issue AD 2003-09-01, Amendment 39-13130 (68 FR 22582, April 29, 2003). AD 2003-09-01 currently requires you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations on Pilatus Model PC-6 airplanes.
The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, notified the FAA of the need to supersede AD 2003-09-01 to address an unsafe condition that may exist or could develop on Model PC-6 airplanes, all manufacturer serial numbers (MSN) up to and including 939. The FOCA reports that the AD action should also apply to all the models of the PC-6 airplanes listed in the type certification data sheet of TC No. 7A15 produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation).
This condition, if not corrected, could result in increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight.
Foreign Airworthiness Authority Information
The FOCA recently issued Swiss AD Number HB 2005-289, effective date August 23, 2005, to ensure the continued airworthiness of all models of the PC-6 airplanes listed in TC No. 7A15, including those produced in the United States under a licensing agreement with Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation).
The State of Design for the Pilatus PC-6 airplanes is Switzerland and the airplanes are 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.
Under this bilateral airworthiness agreement, the FOCA has kept us informed of the situation described above.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we have examined the FOCA's findings, evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design that are certificated for operation in the United States.
This proposed AD would supersede AD 2003-09-01 with a new AD that would retain all the actions of AD 2003-09-01 and would:
Add manufacturer serial numbers (MSN) 2001 through 2092 for all the models of the PC-6 airplanes as listed in TC No. 7A15 and specified in the applicability section. These MSN are the airplanes produced in the United States through a licensing agreement with the Fairchild Republic Company; and
List all the models of the PC-6 airplanes as listed in TC No. 7A15.
Costs of Compliance
We estimate that this proposed AD would affect 49 airplanes in the U.S. registry.
We estimate the following costs to do the proposed inspection and modifications:
[[Page 26893]]
Total cost Labor cost
Parts cost per airplane
Total cost on U.S. operators
7 work hours x $80 per hour = $560.......
$300
$860 $860 x 49 = $42,140.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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.
For the reasons discussed above, I certify that the proposed regulation:
-
Is not a ``significant regulatory action'' under Executive Order 12866;
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Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and
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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.
We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information on the Internet at http://dms.dot.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5227) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
-
The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2003-09-01, Amendment 39-13130, and adding the following new AD:
Pilatus Aircraft LTD.: Docket No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD.
Comments Due Date
(a) We must receive comments on this airworthiness directive (AD) action by June 9, 2006.
Affected ADs
(b) This AD supersedes AD 2003-09-01, Amendment 39-13130.
Applicability
(c) This AD affects the following Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/ C1-H2 airplanes that are equipped with turbo-prop engines and are certificated in any category:
(1) Group 1 (maintains the actions from AD 2003-09-01): All manufacturer serial numbers (MSN) up to and including 939.
(2) Group 2: MSN 2001 through 2092.
Note: These airplanes are also identified as Fairchild Republic Company PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller Corporation PC-6 airplanes.
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland that requires retaining the actions of AD 2003-09-01 and adding MSN 2001 through 2092 for all the models of the PC-6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15. We are issuing this AD to detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight- control system. Such failure could lead to problems in controlling flight.
Compliance
(e) To address this problem, you must do the following:
Actions
Compliance
Procedures
(1) Inspect, before removal (A) For Group 1 Follow Pilatus of the wing bellcrank
Airplanes: Within Aircraft Ltd. PC-6 assemblies, part numbers (P/ the next 100 hours Service Bulletin N) 6132.0071.51 and
time-in-service No. 27-001, dated 6132.0071.52, for installed (TIS) after June June 5, 2002. circlips, P/N N237:
17, 2003 (the (i) If circlips are
effective date of installed, do the actions AD 2003-09-01), required in paragraphs
unless already done. (e)(5) and (e)(6) of this (B) For Group 2 AD.
Airplanes: Within (ii) If circlips are not the next 100 hours installed, perform all
TIS after the actions required by
effective date of paragraphs (e)(3), (e)(4), this AD, unless (e)(5), (e)(6), and (e)(7) already done. of this AD.
[[Page 26894]]
(2) Inspect, before removal Before further
Follow Pilatus of the fuselage bellcrank flight after the Aircraft Ltd. PC-6 assembly, P/N 6232.0118.00, inspection required Service Bulletin for the circlip installed in paragraph (e)(1) No. 27-001, dated on the housing to prevent of this AD.
June 5, 2002. axial movement of the bellcrank on its bearing and the flange of the housing to the rear. If the fuselage bellcrank assembly has either no circlip and/ or it is not installed as required, perform the actions in paragraphs (e)(8) and (e)(9) of this AD. (3) Remove the wing
Before further
Follow Pilatus bellcrank assemblies, P/Ns flight after the Aircraft Ltd. PC-6 6132.0071.51 and
inspections
Service Bulletin 6132.0071.52, and inspect required in
No. 27-001, dated for worn or damaged
paragraphs (e)(1) June 5, 2002. bearings. Replace worn or and (e)(2) of this damaged bearings.
AD, as applicable. (4) Stake and lock the
Before further
Follow Pilatus bearing in the housing of flight after the Aircraft Ltd. PC-6 the wing bellcranks, P/Ns inspections
Service Bulletin 6132.0071.51 and
required in
No. 27-001, dated 6132.0071.52.
paragraphs (e)(1) June 5, 2002. and (e)(2) of this AD, as applicable. (5) Inspect the wing
Before further
Follow Pilatus bellcranks control-cable flight after the Aircraft Ltd. PC-6 attachment bolts for
inspections
Service Bulletin correct type and for signs required in
No. 27-001, dated of rub damage on the heads. paragraphs (e)(1) June 5, 2002. Replace bolts that are
and (e)(2) of this damaged and/or have a total AD. length (including head) of more than 21.5 mm (0.85 in.) (6) Inspect the wing
Before further
Follow Pilatus bellcranks support plate flight after the Aircraft Ltd. PC-6 for signs of rub damage inspections
Service Bulletin caused by the bolts. If required in
No. 27-001, dated damage is found:
paragraphs (e)(1) June 5, 2002. (i) Obtain a repair scheme and (e)(2) of this from the manufacturer
AD. through FAA at the address specified in paragraph (f) of this AD. (ii) Incorporate this repair scheme.. (7) Reinstall wing bellcrank Before further
Follow Pilatus assemblies.
flight after the Aircraft Ltd. PC-6 inspections
Service Bulletin required in
No. 27-001, dated paragraphs (e)(1) June 5, 2002. and (e)(2) of this AD. (8) Remove the fuselage Before further
Follow Pilatus bellcrank assembly, P/N flight after the Aircraft Ltd. PC-6 6232.0118.00, and inspect inspections
Service Bulletin the housing for wear,
required in
No. 27-001, dated damage, and signs of axial paragraphs (e)(1) June 5, 2002. movement of the bearing in and (e)(2) of this the housing. Replace worn AD. or damaged bearings. If any signs of axial movement of a bearing are found: (i) Obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD. (ii) Incorporate this repair scheme.. (9) Reinstall the fuselage Before further
Follow Pilatus bellcrank assembly. Ensure flight after the Aircraft Ltd. PC-6 that the fuselage bellcrank inspections
Service Bulletin assembly is installed so required in
No. 27-001, dated that the surface of the paragraphs (e)(1), June 5, 2002. bellcrank with the flange (e)(2) and (e)(8) of the housing is installed of this AD. to the rear. The effect of this is to lock the bellcrank on the bearing tube and thus prevent movement. (10) Do not install any (A) For Group 1 Follow Pilatus bellcrank assemblies, P/Ns Airplanes: As of Aircraft Ltd. PC-6 6132.0071.51, 6132,0071.52, June 17, 2003 (the Service Bulletin and 6232.0118.00 (or FAA- effective date of No. 27-001, dated approved equivalent part AD 2003-09-01). June 5, 2002. numbers), unless the
(B) For Group 2 aileron assembly has been Airplanes: As of inspected, modified, and the effective date installed.
of this AD.
Note 1: Axial movement of serviceable bearings in the housings of the wing bellcranks is permitted provided no wear or damage to the bearing is found.
Note 2: Any signs of axial movement of a bearing in the housing of the fuselage bellcrank assembly requires that you obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD and incorporate the repair scheme.
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 2003-09-01 are approved for this AD.
Related Information
(h) To get copies of the documents referenced in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC, or on the Internet at http://dms.dot.gov. The docket number is Docket No. FAA-
2006-24092; Directorate Identifier 2006-CE-18-AD.
Issued in Kansas City, Missouri, on May 3, 2006. Barry R. Ballenger, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-7017 Filed 5-8-06; 8:45 am]
BILLING CODE 4910-13-P
