Airworthiness directives: Pilatus Aircraft Ltd.,

[Federal Register: April 29, 2003 (Volume 68, Number 82)]

[Rules and Regulations]

[Page 22582-22584]

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

[DOCID:fr29ap03-5]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-01-AD; Amendment 39-13130; AD 2003-09-01]

RIN 2120-AA64

Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-6 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Model PC-6 airplanes. This AD requires you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations. 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 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: This AD becomes effective on June 17, 2003.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of June 17, 2003.

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. 2003-CE-01-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 all Pilatus Model PC-6 airplanes. The FOCA reports one occurrence where the pilot reported increased friction on the ailerons. Inspection revealed unwanted axial movement of the aileron bellcrank assemblies, part numbers 6132.0071.51, 6132.0071.52, and 6232.0118.00. The axial movement is caused by deterioration of the adhesive bond around the bellcrank bearings which could cause the heads of the control cable attachment bolts to catch on the adjacent structure.

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-6 airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on February 12, 2003 (68 FR 7081). The NPRM proposed to you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations.

What is the potential impact if FAA took no action? Increased friction in the aileron control bellcrank assemblies could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight.

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? We carefully reviewed all available information related to the subject presented above and determined that air safety and the public interest require the adoption of the rule as proposed except for the changes discussed above and minor editorial questions. We have determined that these changes and minor corrections:

[[Page 22583]]

--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 32 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 inspections and modifications:

Total cost Labor cost

Parts cost per airplane

Total cost on U.S. operators

7 workhours x $60 per hour = $420......

$300

$720 $720 x 32 = $23,040.

We have no way of estimating costs to accomplish any necessary repairs that would be required based on the results of the inspections. We have no way of determining the number of airplanes that may need such repair.

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 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

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:

2003-09-01 Pilatus Aircraft Ltd.: Amendment 39-13130; Docket No. 2003-CE-01-AD.

(a) What airplanes are affected by this AD? This AD affects Model PC-6 airplanes, all manufacturer serial numbers (MSN) up to and including 939, 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 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.

(d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following:

Actions

Compliance

Procedures

(1) Inspect, before removal, Within the next 100 In accordance with the wing bellcrank

hours time-in-

Pilatus Aircraft assemblies, part numbers (P/ service (TIS) after Ltd. PC-6 Service N) 6132.0071.51 and

June 17, 2003 (the Bulletin No. 27- 6132.0071.52, for installed effective date of 001, dated June 5, circlips, P/N N237.

this AD), unless 2002, and the already

applicable accomplished.

maintenance manual. (i) If circlips are installed, perform the actions required in paragraphs (d)(5) and (d)(6). (ii) If circlips are not installed, perform all actions required by paragraphs (d)(3), (d)(4), (d)(5), (d)(6), and (d)(7). (2) Inspect, before removal, Prior to further In accordance with the fuselage bellcrank

flight after the Pilatus Aircraft assembly, P/N 6232.0118.00, inspection required Ltd. PC-6 Service for the circlip installed in paragraph (d)(1) Bulletin No. 27- on the housing to prevent of this AD.

001, dated June 5, axial movement of the

2002, and the bellcrank on its bearing

applicable and the flange of the

maintenance manual. housing to the rear. If the fuselage bellcrank assembly has either no circlip and/ or is not installed as required, perform the actions in paragraphs (d)(8) and (d)(9). (3) Remove the wing

Prior to further In accordance with bellcrank assemblies, P/Ns flight after the Pilatus Aircraft 6132.0071.51 and

inspections

Ltd. PC-6 Service 6132.0071.52, and inspect required in

Bulletin No. 27- for worn or damaged

paragraphs (d)(1) 001, dated June 5, bearings. Replace worn or and (d)(2) of this 2002, and the damaged bearings.

AD, as applicable. applicable maintenance manual. (4) Stake and lock the

Prior to further In accordance with bearing in the housing of flight after the Pilatus Aircraft the wing bellcranks, P/Ns inspections

Ltd. PC-6 Service 6132.0071.51 and

required in

Bulletin No. 27- 6132.0071.52.

paragraphs (d)(1) 001, dated June 5, and (d)(2) of this 2002, and the AD, as applicable. applicable maintenance manual.

[[Page 22584]]

(5) Inspect the wing

Prior to further In accordance with bellcranks control-cable flight after the Pilatus Aircraft attachment bolts for

inspections

Ltd. PC-6 Service correct type and for signs required in

Bulletin No. 27- of rub damage on the heads. paragraphs (d)(1) 001, dated June 5, Replace bolts which are and (d)(2) of this 2002, and the damaged and/or have a total AD.

applicable length (including head) of

maintenance manual. more than 21.5 mm (0.85 in.). (6) Inspect the wing

Prior to further In accordance with bellcranks support plate flight after the Pilatus Aircraft for signs of rub damage inspections

Ltd. PC-6 Service caused by the bolts. If required in

Bulletin No. 27- damage is found:.

paragraphs (d)(1) 001, dated June 5, and (d)(2) of this 2002, and the AD.

applicable maintenance manual. (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. (7) Reinstall wing bellcrank Prior to further In accordance with assemblies.

flight after the Pilatus Aircraft inspections

Ltd. PC-6 Service required in

Bulletin No. 27- paragraphs (d)(1) 001, dated June 5, and (d)(2) of this 2002, and the AD.

applicable maintenance manual. (8) Remove the fuselage Prior to further In accordance with bellcrank assembly, P/N flight after the Pilatus Aircraft 6232.0118.00, and inspect inspections

Ltd. PC-6 Service the housing for wear,

required in

Bulletin No. 27- damage, and signs of axial paragraphs (d)(1) 001, dated June 5, movement of the bearing in and (d)(2) of this 2002, and the the housing. Replace worn AD.

applicable or damaged bearings. If any

maintenance manual. 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 Prior to further In accordance with bellcrank assembly. Ensure flight after the Pilatus Aircraft that the fuselage bellcrank inspections

Ltd. PC-6 Service assembly is installed so required in

Bulletin No. 27- that the surface of the paragraphs (d)(1), 001, dated June 5, bellcrank with the flange (d)(2) and d)(8) of 2002, and the of the housing is installed this AD.

applicable to the rear. The effect of

maintenance manual. this is to lock the bellcrank on the bearing tube and thus prevent movement. (10) Do not install any As of June 17, 2003 In accordance with bellcrank assemblies, P/Ns (the effective date Pilatus Aircraft 6132.0071.51, 6132,0071.52, of this AD).

Ltd. PC-6 Service and 6232.0118.00 (or FAA-

Bulletin No. 27- approved equivalent part

001, dated June 5, numbers), unless the

2002, and the aileron assembly has been

applicable inspected, modified, and

maintenance manual. installed.

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.

(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 3: 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 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 Aircraft Ltd. PC-6 Service Bulletin No. 27-001, dated June 5, 2002. 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 4: The subject of this AD is addressed in Swiss AD Number HB 2002-642, dated November 15, 2002.

(i) When does this amendment become effective? This amendment becomes effective on June 17, 2003.

Issued in Kansas City, Missouri, on April 18, 2003. Dorenda D. Baker, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 03-10237 Filed 4-28-03; 8:45 am]

BILLING CODE 4910-13-P