Airworthiness directives: Pilatus Aircraft Ltd.,

[Federal Register: November 3, 2005 (Volume 70, Number 212)]

[Rules and Regulations]

[Page 66749-66752]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr03no05-2]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21835; Directorate Identifier 2005-CE-35-AD; Amendment 39-14357; AD 2005-22-13]

RIN 2120-AA64

Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to inspect the left and right main landing gear (MLG) assemblies for any part number (P/N) 532.10.12.077 or FAA- approved equivalent part number bolts that do not have white primed and painted heads; and replace any bolt found with new P/N 532.10.12.077F or FAA-approved equivalent part number bolts in all MLG assemblies. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct any P/N 532.10.12.077 or FAA- approved equivalent part number bolts that do not have white primed and painted heads, which could result in corrosion of the bolt and consequent failure of the bolt. This failure could lead to MLG collapse during airplane landing and take-off operations with consequent loss of airplane control.

DATES: This AD becomes effective on December 19, 2005.

As of December 19, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation.

ADDRESSES: To get the service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e- mail: SupportPC12@pilatus-aircraft.com or from Pilatus Business Aircraft Ltd., Product Support Department, 11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-9099; facsimile: (303) 465-6040.

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 20590-0001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-21835; Directorate

Identifier 2005-CE-35-AD.

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 Models PC-12 and PC-12/45 airplanes. The FOCA reports part number (P/N) 532.10.12.077 bolts that do not have white primed and painted heads are subject to corrosion. These bolts attach the hydraulic actuators to the left and right main landing gear (MLG) assemblies. The FOCA further reports the separation of a bolt head in an MLG assembly has occurred due to corrosion. The corrosion occurred because the bolt head was not primed and painted.

[[Page 66750]]

Pilatus has designed and produced a new bolt (P/N 532.10.12.077F) as part of Modification Kit No. 500.50.12.299 to replace the subject bolt. Pilatus recommends the replacement of bolts in pairs.

What is the potential impact if FAA took no action? Corrosion of the bolt could lead to MLG collapse during airplane landing and take- off operations with consequent loss of airplane control.

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 Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on August 2, 2005 (70 FR 44297). The NPRM proposed to require you to inspect the left and right main landing gear (MLG) assemblies for any part number (P/N) 532.10.12.077 bolts that do not have white primed and painted heads; and replace any bolt found with new P/N 532.10.12.077F bolts in all MLG assemblies.

Comments

Was the public invited to comment? We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA's response to each comment:

Comment Issue: Include Parts Manufacture Approval (PMA) Parts Approved by Identicality in Both the Parts Replaced and the Replacement Parts

What is the commenters' concern? Two commenters specifically ask that the FAA address PMA parts approved by identicality in both the parts replaced (unsafe condition) and the replacement parts (correction of condition). Specifically, the commenters state:

1. One commenter believes FAA should add the phrase ``or FAA- approved equivalent part number'' to the replacement part as it did with the parts replaced; and

2. Another commenter states that restricting parts to be replaced and parts installed to just those cited in the manufacturer service bulletin is not good form and might establish a dangerous precedent. The commenter believes that installed PMA parts could have the same unsafe condition and that the owner/operator should have the option of installing equivalent parts without applying for an alternative method of compliance (AMOC). The commenter also believes that the phrase ``or FAA-approved equivalent part number'' is inadequate for replacement parts and proposes language to clarify that phrase.

   What is FAA's response to the concern? The FAA concurs with all the comments above. The FAA will add information to further clarify the phrase ``or FAA-approved equivalent part number'', and add the phrase to cover the PMA replacement parts.

   Conclusion

   What is FAA's final determination on this issue? We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for the changes discussed above and minor editorial corrections. We have determined that these changes and minor corrections:

   --Are consistent with 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.

   Docket Information

   Where can I go to view the docket information? You may view the AD docket that contains information relating to this subject in person at the DMS Docket Offices between 9:00 a.m. and 5:00 p.m. (eastern time), Monday through Friday, except Federal holidays. The Docket Office (telephone 1-800-647-5227) is located on the plaza level of the Department of Transportation NASSIF Building at the street address stated in ADDRESSES. You may also view the AD docket on the Internet at http://dms.dot.gov.

   Changes to 14 CFR Part 39--Effect on the AD

   How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions.

   Costs of Compliance

   How many airplanes does this AD impact? We estimate that this AD affects 350 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 do the inspection:

   Total cost per Total cost on Labor cost

   Parts cost

   airplane U.S. operators

   1 work hour x $65 per hour = $65............ Not applicable................

   $65

   $22,750

   We estimate the following costs to do any necessary single bolt replacement (using Modification Kit No. 500.50.12.299) that would be required based on the results of this inspection. We have no way of determining the number of airplanes that may need this bolt replacement:

   Total cost per Labor cost

   Parts cost

   airplane

   3 work hours x $65 per hour = $1,000 estimate for

   $1,195 $195.

   each Modification Kit No. 500.50.12.299.

   Pilatus will provide warranty credit for inspecting and replacing the specified bolts to the extent stated in the service information.

   Authority for This Rulemaking

   What authority does FAA have for issuing this rulemaking action? 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

   [[Page 66751]]

   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 AD.

   Regulatory Findings

   Will this AD impact various entities? We have determined that this AD will not have federalism implications under Executive Order 13132. This AD 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.

   Will this AD involve a significant rule or regulatory action? For the reasons discussed above, I certify that this AD:

1. Is not a ``significant regulatory action'' under Executive Order 12866;

2. Is not a ``significant rule'' under the 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.

   We prepared a summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ``Docket No. FAA-2005-21835; Directorate Identifier 2005-CE-35-AD'' in your request.

   List of Subjects in 14 CFR Part 39

   Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

   Adoption of the Amendment

   0 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

   0 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]

   0 2. FAA amends Sec. 39.13 by adding a new AD to read as follows:

   2005-22-13 Pilatus Aircraft Ltd.: Amendment 39-14357; Docket No. FAA-2005-21835; Directorate Identifier 2005-CE-35-AD.

   When Does This AD Become Effective?

   (a) This AD becomes effective on December 19, 2005.

   What Other ADs Are Affected by This Action?

   (b) None.

   What Airplanes Are Affected by This AD?

   (c) This AD affects Models PC-12 and PC-12/45 airplanes, Manufacturers Serial Numbers (MSN) 101 through 620, that are certificated in any category.

   What Is the Unsafe Condition Presented in This AD?

   (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to detect and correct any part number (P/N) 532.10.12.077 or FAA-approved equivalent part number bolts that do not have white primed and painted heads, which could result in corrosion of the bolt and consequent failure of the bolt. This failure of the bolt could lead to main landing gear (MLG) collapse during airplane landing and take-off operations with consequent loss of airplane control.

   What Must I Do To Address This Problem?

   (e) To address this problem, you must do the following:

   Actions

   Compliance

   Procedures

   (1) Inspect the main landing Within the next 100 Follow Pilatus PC12 gear (MLG) assemblies, part hours time-in-

   Service Bulletin number (P/N) 532.10.12.049 service (TIS) or 90 No. 32-018, dated and P/N 532.10.12.050 or days after December May 2, 2005. FAA-approved equivalent 19, 2005 (the part number, for any P/N effective date of 532.10.12.077 or FAA-

   this AD), whichever approved equivalent part occurs first, number bolts that do not unless already done. have white primed and painted heads. (2) Replace any P/N

   Before further

   Follow Pilatus PC12 532.10.12.077 bolts that do flight after

   Service Bulletin not have white primed and inspection required No. 32-018, dated painted heads found as a by paragraph (e)(1) May 2, 2005. result of the inspection of this AD. required by paragraph (e)(1) of this AD. Replace with new bolts (new P/N 532.10.12.077F or FAA- approved equivalent part number) in both MLG assemblies. (3) 14 CFR 21.303 allows for Not Applicable...... Not Applicable. replacement parts through parts manufacturer approval (PMA). The phrase ``or FAA- approved equivalent part number'' in this AD is intended to signify those parts that are PMA parts approved through identicality to the design of the part under the type certificate and replacement parts to correct the unsafe condition under PMA (other than identicality). If parts are installed that are identical to the unsafe parts, then the corrective actions of the AD affect these parts also. In addition, equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may also be installed provided they meet current airworthiness standards, which include those actions cited in this AD.

   [[Page 66752]]

   (4) Do not install:

   (i) Any P/N 532.10.12.077 (or FAA- approved equivalent part number) bolt that does not have a white primed and painted head in any MLG assembly (P/ N 532.10.12.049, P/N 532.10.12.050, or FAA- approved equivalent part number); and

   (ii) Any MLG assembly (P/ As of December 19, Not Applicable. N 532.10.12.049, P/N 2005 (the effective 532.10.12.050 or FAA- date of this AD). approved equivalent part number) that does not have P/N 532.10.12.077F (or FAA- approved equivalent part number) bolts with white primed and painted heads.

   Note: The FAA recommends that you return any removed bolts to Pilatus.

   May I Request an Alternative Method of Compliance?

   (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, 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.

   Is There Other Information That Relates to This Subject?

   (g) Swiss AD Number HB-2005-288, dated June 29, 2005, also addresses the subject of this AD.

   Does This AD Incorporate Any Material by Reference?

   (h) You must do the actions required by this AD following the instructions in Pilatus PC12 Service Bulletin No. 32-018, dated May 2, 2005. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e-mail: SupportPC12@pilatus-aircraft.com or from Pilatus Business Aircraft Ltd., Product Support Department, 11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465- 9099; facsimile: (303) 465-6040. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. 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 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-21835;

   Directorate Identifier 2005-CE-35-AD.

   Issued in Kansas City, Missouri, on October 25, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

   [FR Doc. 05-21803 Filed 11-2-05; 8:45 am]

   BILLING CODE 4910-13-P