AD 98-05-06
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Pilatus Aircraft Limited | PC-12 | Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-12 Airplanes |
Unsafe Condition
Fatigue damage to the elevator due to incorrect rivet lengths or excessive gaps in rivet shanks, which could result in structural failure and eventual loss of control of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the elevator for incorrect rivet lengths and excessive gaps in rivet shanks within 200 hours time-in-service after the effective date. Install new rivets and shims as required, prior to further flight, following Pilatus Service Bulletin No. 55-001.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 200 hours time-in-service after 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-12 airplanes with manufacturer’s serial numbers 101, 105, 106, 107, 109 through 112, 114, 115, 117 through 120, 122 through 125, 129, 131 through 140, 142, and 146; certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Elevator Rivet Lengths
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_98-05-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-05-06 Document Type: AD Final Rules Docket Number: 97-CE-98-AD Subject Heading: Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-12 Airplanes Subject: Elevator Rivet Lengths Status: Current Citation: Federal Register: April 22, 1998 (Volume 63, Number 77) Citation Publish Date: 04/22/1998 Effective Date: 05/29/1998 Make: Pilatus Aircraft Limited Model: PC-12 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 [63 FR 19798 No. 77 04/22/98] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-05-06 CITATION: [Federal Register: April 22, 1998 (Volume 63, Number 77)] PAGE NUMBER: [Page 19798] DOCKET NUMBER: 97-CE-98-AD AMENDMENT: 39-10367 AD NUMBER: 98-05-06 SUBJECT HEADING: Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-12 Airplanes ACTION: Direct final rule; confirmation of effective date. SUMMARY: This action confirms the effective date of Airworthiness Directive (AD) 98-05-06, which applies to Pilatus Aircraft Ltd. (Pilatus) Model PC-12 airplanes. AD 98-05-06 requires inspecting the elevator for incorrect rivet lengths and installing new rivets if incorrect rivet lengths are found. This AD also requires inspecting the elevator to assure that an excessive gap (more than .004 inches or .1 millimeters (mm)) does not exist in the rivet shanks, and installing a shim between the rib and skin to fill any excessive gap. 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 prevent fatigue damage to the elevator, which could result in structural failure and eventual loss of control of the airplane. DATES: Effective May 29, 1998. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Mr. Roman T. Gabrys, Aerospace Engineer, Small Airplane Directorate, Airplane Certification Service, FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106; telephone: (816) 426-6932; facsimile: (816) 426-2169. SUPPLEMENTARY INFORMATION: The FAA published this direct final rule with request for comments in the Federal Register on March 3, 1998 (63 FR 10299). The FAA uses the direct final rulemaking procedure for a non-controversial rule where the FAA anticipates that there will be no adverse public comment. This direct final rule advised the public that no adverse comments were anticipated, and that unless a written adverse comment, or a written notice of intent to submit such an adverse comment, was received within the comment period, the regulation would become effective on May 29, 1998. No adverse comments were received, and thus this notice confirms that this final rule will become effective on that date. REGULATORY TEXT: 98-05-06 PILATUS AIRCRAFT LTD: Amendment 39-10367; Docket No. 97-CE-98-AD. Applicability: Model PC-12 airplanes, manufacturer’s serial numbers (MSN) 101, 105, 106, 107, 109 through 112, 114, 115, 117 through 120, 122 through 125, 129, 131 through 140, 142, and 146; 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 as indicated in the body of this AD, unless already accomplished. To prevent fatigue damage to the elevator, which could result in structural failure and eventual loss of control of the airplane, accomplish the following: (a) Within the next 200 hours time-in-service (TIS) after the effective date of this AD, inspect the elevator for incorrect rivet lengths in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Pilatus Service Bulletin No. 55-001, dated November 8, 1996. Prior to further flight, install new rivets if incorrect rivet lengths are found in accordance with the above-referenced service bulletin. (b) Within the next 200 hours TIS after the effective date of this AD, inspect the elevator to assure that an excessive gap (more than .004 inches or .1 millimeters (mm)) does not exist in the rivet shanks in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Pilatus Service Bulletin No. 55-001, dated November 8, 1996. Prior to further flight, install a shim between the rib and skin to fill any excessive gap in accordance with the above-referenced service bulletin. (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 compliance time that provides an equivalent level of safety may be used if approved by the Manager, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City, Missouri 64106. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Small Airplane Directorate. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate. (e) Questions or technical information related to Pilatus Service Bulletin No. 55-001, dated November 8, 1996, should be directed to Pilatus Aircraft Ltd., Marketing Support Department, CH-6370 Stans, Switzerland; telephone: +41 41-6196 233; facsimile: +41 41-6103 351. This service information may be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City. (f) The inspection and installations required by this AD shall be done in accordance with Pilatus Service Bulletin No. 55-001 dated November 8, 1996. 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 Pilatus Aircraft Ltd., Marketing Support Department, CH-6370 Stans, Switzerland. Copies may be inspected at the FAA, Central Region, Office of the Regional 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. NOTE 3: The subject of this AD is addressed in Swiss AD HB 96-535A, dated November 30, 1996, corrected January 28, 1998. (g) This amendment (39-10367) becomes effective on May 29, 1998. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_98-05-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-05-06 Document Type: AD Final Rules Docket Number: 97-CE-98-AD Subject Heading: Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-12 Airplanes Subject: Elevator Rivet Lengths Status: Current Citation: Federal Register: April 22, 1998 (Volume 63, Number 77) Citation Publish Date: 04/22/1998 Effective Date: 05/29/1998 Make: Pilatus Aircraft Limited Model: PC-12 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 [63 FR 19798 No. 77 04/22/98] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-05-06 CITATION: [Federal Register: April 22, 1998 (Volume 63, Number 77)] PAGE NUMBER: [Page 19798] DOCKET NUMBER: 97-CE-98-AD AMENDMENT: 39-10367 AD NUMBER: 98-05-06 SUBJECT HEADING: Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-12 Airplanes ACTION: Direct final rule; confirmation of effective date. SUMMARY: This action confirms the effective date of Airworthiness Directive (AD) 98-05-06, which applies to Pilatus Aircraft Ltd. (Pilatus) Model PC-12 airplanes. AD 98-05-06 requires inspecting the elevator for incorrect rivet lengths and installing new rivets if incorrect rivet lengths are found. This AD also requires inspecting the elevator to assure that an excessive gap (more than .004 inches or .1 millimeters (mm)) does not exist in the rivet shanks, and installing a shim between the rib and skin to fill any excessive gap. 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 prevent fatigue damage to the elevator, which could result in structural failure and eventual loss of control of the airplane. DATES: Effective May 29, 1998. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Mr. Roman T. Gabrys, Aerospace Engineer, Small Airplane Directorate, Airplane Certification Service, FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106; telephone: (816) 426-6932; facsimile: (816) 426-2169. SUPPLEMENTARY INFORMATION: The FAA published this direct final rule with request for comments in the Federal Register on March 3, 1998 (63 FR 10299). The FAA uses the direct final rulemaking procedure for a non-controversial rule where the FAA anticipates that there will be no adverse public comment. This direct final rule advised the public that no adverse comments were anticipated, and that unless a written adverse comment, or a written notice of intent to submit such an adverse comment, was received within the comment period, the regulation would become effective on May 29, 1998. No adverse comments were received, and thus this notice confirms that this final rule will become effective on that date. REGULATORY TEXT: 98-05-06 PILATUS AIRCRAFT LTD: Amendment 39-10367; Docket No. 97-CE-98-AD. Applicability: Model PC-12 airplanes, manufacturer’s serial numbers (MSN) 101, 105, 106, 107, 109 through 112, 114, 115, 117 through 120, 122 through 125, 129, 131 through 140, 142, and 146; 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 as indicated in the body of this AD, unless already accomplished. To prevent fatigue damage to the elevator, which could result in structural failure and eventual loss of control of the airplane, accomplish the following: (a) Within the next 200 hours time-in-service (TIS) after the effective date of this AD, inspect the elevator for incorrect rivet lengths in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Pilatus Service Bulletin No. 55-001, dated November 8, 1996. Prior to further flight, install new rivets if incorrect rivet lengths are found in accordance with the above-referenced service bulletin. (b) Within the next 200 hours TIS after the effective date of this AD, inspect the elevator to assure that an excessive gap (more than .004 inches or .1 millimeters (mm)) does not exist in the rivet shanks in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Pilatus Service Bulletin No. 55-001, dated November 8, 1996. Prior to further flight, install a shim between the rib and skin to fill any excessive gap in accordance with the above-referenced service bulletin. (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 compliance time that provides an equivalent level of safety may be used if approved by the Manager, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City, Missouri 64106. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Small Airplane Directorate. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate. (e) Questions or technical information related to Pilatus Service Bulletin No. 55-001, dated November 8, 1996, should be directed to Pilatus Aircraft Ltd., Marketing Support Department, CH-6370 Stans, Switzerland; telephone: +41 41-6196 233; facsimile: +41 41-6103 351. This service information may be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City. (f) The inspection and installations required by this AD shall be done in accordance with Pilatus Service Bulletin No. 55-001 dated November 8, 1996. 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 Pilatus Aircraft Ltd., Marketing Support Department, CH-6370 Stans, Switzerland. Copies may be inspected at the FAA, Central Region, Office of the Regional 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. NOTE 3: The subject of this AD is addressed in Swiss AD HB 96-535A, dated November 30, 1996, corrected January 28, 1998. (g) This amendment (39-10367) becomes effective on May 29, 1998. FOOTER:
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Retrieved: Apr 8, 2026
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